# Perturbations from ducts on the modes of acoustic thermometers.

We examine the perturbations of the modes of the an acoustic
thermometer caused by circular ducts used either for gas flow or as
acoustic waveguides coupled to remote transducers. We calculate the
acoustic admittance of circular ducts using a model based on
transmission line theory. The admittance is used to calculate the
perturbations to the resonance frequencies and half-widths of the modes
of spherical and cylindrical acoustic resonators as functions of the
duct's radius, length, and the locations of the transducers along
the duct's length. To verify the model, we measured the complex
acoustic admittances of a series of circular tubes as a function of
length between 200 Hz and 10 kHz using a three-port acoustic coupler.
The absolute magnitude of the specific acoustic admittance is
approximately one. For a 1.4 mm inside-diameter, 1.4 m long tube, the
root mean square difference between the measured and modeled specific
admittances (both real and imaginary parts) over this frequency range
was 0.018. We conclude by presenting design considerations for ducts
connected to acoustic thermometers.

Key words: acoustic resonator; acoustic thermometry; Boltzmann constant; duct; perturbation; waveguide.

1. Introduction

Acoustic thermometers determine the thermodynamic temperature of dilute, high-purity argon or helium by measuring the acoustic resonance frequencies of a gas-filled cavity (1), (2), (3), (4), (5), (6), (7). Because these resonances have high quality factors, one can measure the frequencies with relative uncertainties of [10.sup.-6] or less. Therefore, uncertainty in determining the thermodynamic temperature results from other factors such as impurities in the gas or imperfections of the model for a particular resonator. The model must account for ducts used to flow gas into and out of the resonant cavity as well as crevices at seams joining sections of the cavity's wall. At high temperatures, the gas under study may be contaminated by outgassing water, hydrogen, etc. Flowing high-purity gas through the resonator via ducts (long, thin tubes) effectively mitigates the problem of outgassing (3), (4), (5). Ducts are also useful as acoustic waveguides to transmit sound between a resonator at high temperature and transducers located near ambient temperature (8), (9). This practice circumvents the problem of manufacturing efficient, stable electroacoustic transducers and cables that function at high temperatures.

In this paper, we calculate the perturbations of the acoustic resonances of gas-filled cavities caused by circular ducts used either for gas flow or as acoustic waveguides coupled to remote transducers. First, we review the well-established model for the acoustic admittance of circular ducts based on transmission line theory (10), (11), (12), (13). We calculate the perturbations to the resonance frequencies and half-widths of the modes of spherical and cylindrical acoustic cavities as functions of the duct's radius, length, and also as a function of the location of the transducers along the duct's length. To verify the model for a circular duct, we measured the complex acoustic admittances of a series of circular tubes as a function of length between 200 Hz and 10 kHz using a three-port acoustic coupler. Over this frequency range, the root mean square difference between the measured and modeled specific admittances of a 1.4 mm ID, 1.4 m long tube was 0.018. We conclude by discussing design considerations for ducts leading to acoustic thermometers.

2. Acoustic Model for Circular Ducts

See Refs. (12) and (13), and references cited therein, for a detailed description of the acoustic model for a duct with a circular cross section. The model is valid for frequencies below the "cutoff frequency" [f.sub.co], the frequency below which only plane waves propagate. If the duct's radius is [r.sub.d] and the speed of sound in the gas is c, then [f.sub.co] [approximately equal to] 0.29 [c/[r.sub.d]] or about 140 kHz for ambient air in a 1.4 mm ID duct. We adopt the [e.sup.i[omega]t] time dependence convention, consistent with Refs. (12) and (13). We restrict the discussion to ducts with length [l.sub.d] [much greater than] [r.sub.d] and thereby neglect the effects of non-planar flow and sharp corners at the ends of the ducts (12). Finally, we assume that the cross-sectional area of the duct [A.sub.d] = [pi][r.sub.d.sup.2] is a small fraction of the resonator's surface area.

The model's central result is that the acoustic pressure [[~.p].sub.[+ or -]] and volume velocity [[~.U].sub.[+ or -]] of damped traveling waves in a duct are plane waves proportional to [e.sup.[[+ or -][GAMMA][z+i][omega]t]], where the propagation constant [GAMMA] is given by

[GAMMA] = [i[omega]/c][square root of [[1 + ([gamma] - 1)[F.sub.t]]/[1 - [F.sub.v]]]]. (1)

Furthermore, the ratios [[~.p].sub.+]/[[~.U].sub.+] and [[~.p].sub.-]/[[~.U].sub.-] define the characteristic impedance [Z.sub.0] of the medium in the duct

[Z.sub.0] = [[rho]c/[A.sub.d]][1/[[square root of (1 - [F.sub.v])[1 + ([gamma] - 1)[F.sub.t]]]]. (2)

The real part of [GAMMA] is a measure of the damping of these traveling waves; [Z.sub.0] determines the phase between [[~.p].sub.[+ or -]] and [[~.U].sub.[+ or -]]. The quantities [F.sub.v] and [F.sub.t] are functions of frequency that account for thermoacoustic dissipation near the duct wall. For a duct with radius [r.sub.d], the thermal loss function is

[F.sub.t][equivalent to][[2[J.sub.1]([[zeta].sub.t])]/[[[zeta].sub.t][J.sub.0]([[zeta].sub.t])]], [[zeta].sub.t] = (1 - i)[r.sub.d]/[[delta].sub.t] (3)

where [J.sub.0] and [J.sub.1] are Bessel functions and [[delta].sub.t]= [square root of [2[[lambda].sub.t]/([rho][C.sub.P][omega])]] is the thermal boundary layer thickness. The viscous loss function [F.sub.v] has the same form as Eq. (3) with [[delta].sub.t] replaced by the viscous boundary layer thickness [[delta].sub.v] = [square root of [2[eta]/[rho][omega]]]. For the gas |properties in these expressions, [rho] is the density, c is the speed of sound, [eta] is the shear viscosity, [[lambda].sub.t] is the thermal conductivity, [C.sub.P] is the isobaric heat capacity per unit mass, [C.sub.v] is the isochoric heat capacity per unit mass, and [gamma] is the heat capacity ratio [C.sub.P]/[C.sub.v]. [F.sub.v] and [F.sub.t] are complex-valued functions of [[delta].sub.v]/[r.sub.d] and [[delta].sub.t]/[r.sub.d], respectively. The length scales [[delta].sub.t] and [[delta].sub.v] are not independent but are related via the Prandtl number Pr = [eta][C.sub.P]/[[lambda].sub.t] by the expression [[delta].sub.v] = [[delta].sub.t] [square root of Pr.]. Since Pr for monatomic gases is a weak function of temperature and pressure, we describe the damping of waves in a duct in terms of [[delta].sub.t]/[r.sub.d] only.

The model for finite-length tubes includes reflections from the ends. The interference between these counter-propagating waves produces standing waves at particular frequencies. Such tube resonances pose a problem if they occur too close in frequency to the cavity's modes used for thermometry and are insufficiently damped. To model a tube with finite length, we use a lumped-element equivalent circuit defined by a T-network as described in Ref. (12). The input impedance of a tube with length [l.sub.d], terminated by an acoustic impedance [Z.sub.T] is

[Z.sub.in] = [Z.sub.0][[[Z.sub.T] + [Z.sub.0]tanh([GAMMA][l.sub.d])]/[[Z.sub.0] + [Z.sub.T]tanh([GAMMA][l.sub.d])]]. (4)

In the following sections, we investigate the perturbation that such a tube or combinations of tubes has on the modes of acoustic resonators.

3. Perturbation of the Modes of an Acoustic Cavity by Ducts

Consider the acoustic modes of a gas in a closed cavity. The acoustic velocity potential [PSI] for the mode N is a solution to the homogeneous Helmholtz Equation

[[nabla].sup.2][[PSI].sub.N] + [[kappa].sub.N.sup.2][[PSI].sub.N] = 0 (5)

and satisfies a set of boundary conditions defined by the properties of the gas and the shape of the cavity. [The "acoustic" fields (velocity, pressure, and temperature) are the propagating solutions of the linearized equations of motion. The diffusing solutions (thermal and shear evanescent waves) are important near the boundary and define the acoustic boundary layers.] We assume here that [[PSI].sub.N] and the eigenvalue [[kappa].sub.N] are known (either from analytical or numerical calculation) and describe the mode of our "unperturbed" resonator. For simplicity, we assume that the mode is non-degenerate. Acoustic resonators typically have holes in the wall to admit/remove gas and ports for acoustic transducers. For measurements at extreme temperatures, it may be necessary to use small tubes (ducts) as acoustic waveguides to convey sound to and from remote transducers. Changes to the cavity wall such as these change the boundary conditions on the acoustic wave in the vicinity and, therefore, slightly alter [[PSI].sub.N] and [[kappa].sub.N]. For metrology applications, these perturbations must be quantified with high accuracy.

We focus on spherical, quasi-spherical, and cylindrical cavities. Each shape has advantages. Spherical cavities are characterized by a single length (the radius). Quasi-spherical cavities are nearly spherical cavities with a known shape perturbation that splits the degeneracy of the microwave modes and the non-radial acoustic modes of a perfect sphere. The radially-symmetric modes of a gas-filled quasi-spherical cavity are affected by the shape perturbation only in the second order. Thus, the first-order results in this paper for spherical cavities apply to quasi-spherical cavities as well. Since the wave velocity of a radial mode in a spherical cavity is normal to the cavity's wall, there is no viscous boundary layer dissipation. Therefore, the quality factors (Q) of radial modes in spherical cavities are substantially higher than the Qs of modes in nonspherical cavities with the same volume.

The modes of a fixed-length cylindrical cavity are determined by two parameters: its radius and its length. An acoustic interferometer is a cylindrical resonator in which one end is a moveable piston, so that the cavity's length is variable. The interferometer is operated at a fixed frequency while the length is varied through a succession of resonances (14). With the interferometer, the speed of sound is determined not from an absolute length but from the measured displacement of the piston between successive resonances. Furthermore, since the measurements are at fixed frequency, the perturbations from the end plates cancel out to first order. An alternative to the interferometer, which avoids the complications of a moveable piston, uses two cylindrical resonators in which the length of one is twice the length of the other. The modes of the shorter cavity occur at the same frequencies as the even-order modes of the longer cavity. The combined measurements from both cavities at the same frequencies also have the advantage that the perturbations from the endplates cancel to first order.

The theory for calculating boundary perturbations has been published elsewhere (15). From first-order perturbation theory, the shift of the eigenvalue [[kappa].sub.N] due to a non-uniform surface admittance is

[[[[DELTA][K.sub.N]]/[[kappa].sub.N]]][approximately equal to][[i[omega]]/[2c[[kappa].sub.N.sup.2]]][[[[integral].sub.S][[PSI].sub.N.sup.2]y([omega], [r.sub.S])dS]/[[[integral].sub.V][[PSI].sub.N.sup.2]dV]] (6)

where y([omega], [r.sub.s]) is the specific acoustic admittance at point [r.sub.s] on the boundary. In terms of the acoustic velocity [[~.u].sub.ac] and the acoustic pressure [~.p], y([omega], [r.sub.s]) is defined as

y([omega], [r.sub.S]) = [[[rho]c[^.n] * [[~.u].sub.ac]([omega], [r.sub.S])]/[[~.p]([omega], [r.sub.S])]] (7)

where [^.n] is the outward pointing normal unit vector at [r.sub.s].

For the ideal resonator, the walls are assumed to have zero admittance. The presence of the duct changes the shape from the perfect resonator and therefore changes the mode wavenumbers, because the acoustic wave propagates into the duct and may be partially reflected back into the resonator. Furthermore, a lossy duct causes additional thermoacoustic dissipation. Thus, the acoustic wave in the resonator locally "feels" a larger admittance at the entrance to the duct than at the cavity's wall. If the duct's diameter is small compared to the cavity's diameter, then the long-wavelength acoustic waves will not vary appreciably over the cross section of the duct; therefore, we can expand [PSI] about the duct position [r.sub.d] and use the average admittance of the duct over its cross section [[bar.y].sub.d]. The leading term in the approximation to the surface integral in Eq. (6) is

[[integral].sub.S][[[[PSI].sub.N]([r.sub.S])].sup.2]y([omega], [r.sub.S])dS[approximately equal to][[bar.y].sub.d]([omega])[[[[PSI].sub.N]([r.sub.d])].sup.2][A.sub.d]. (8)

The wavenumber for the nth radial mode of a spherical resonator with radius a is changed by a fractional amount, from Eq. (6),

[[[DELTA][K.sub.n]]/[[kappa].sub.n]][approximately equal to][[i[[bar.y].sub.d][A.sub.d]]/[4[pi][a.sup.2][z.sub.0n]]], (9)

where [z.sub.0n] denotes the nth zero of [dj.sub.0](x)/dx, n = 2, 3, 4, ... Because of the spherical symmetry, the perturbation of the radial-mode wavenumbers does not depend on the location of the duct.

For the lth longitudinal mode of a cylindrical resonator with radius R and length L, Eq. (6) becomes

[[[DELTA][K.sub.l]]/[[kappa].sub.l]][approximately equal to][[i[[bar.y].sub.d][A.sub.d]]/[l[[pi].sup.2][R.sup.2]]][cos.sup.2](l[pi][z.sub.d]/L) (10)

where 0 [less than or equal to] [z.sub.d] [less than or equal to] L is the axial location of the duct and l = 1, 2, 3, ... The first-order perturbation of longitudinal modes when the duct mounted on an endplate ([z.sub.d] = 0, L) is independent of where on the endplate the duct is located. The position of the duct [z.sub.d] must be chosen carefully based on the duct's purpose. For ducts used with remote transducers, there is a competition between the desire for small perturbations and the desire for efficient coupling with the acoustic modes of the resonator. The perturbation will be smallest when the duct is placed near a pressure node, i.e., 2l[z.sub.d]/L = 1, 3, 5, ...; however, at this location the coupling between the mode and the transducers is least efficient. The perturbation will be largest when the duct is placed near a pressure anti-node, i.e., 2l[z.sub.d]/L = 0, 2, 4, 6, ... and the coupling will be most efficient. Node placement is a good choice if the duct's purpose is to flow gas into and out of the resonator; however, it may be a bad choice if the duct is a wave-guide leading to a remote transducer. When the cavity's length is fixed, the locations of the pressure nodes and anti-nodes on the cylindrical wall depend on the mode. With an interferometer, the cavity length is varied between two extremes [L.sub.min] and [L.sub.max], and the frequency (and therefore wavelength) is held constant. Therefore, the locations of the pressure nodes and anti-nodes are fixed in space. This feature of the interferometer suggests that an arrangement where the acoustic waveguides are located on the fixed endplate to maximize the coupling to all the modes, and the fill ducts are attached to the side of the resonator at [z.sub.d] = [L.sub.min]/2 at the pressure node. The disadvantage to this arrangement is that it only works for the odd-symmetry modes, which are susceptible to the effects of center-of-mass motion. A better method is to locate the fill ducts and the waveguides on the endplates, study only the even-symmetry modes (to avoid center-of-mass motion), and rely on the cancellation of the first-order perturbations.

In the following sections, we model the acoustic admittance of several duct geometries. Then we estimate the perturbations due to the duct on the radial modes of a 5 cm radius spherical resonator and on the longitudinal modes of a 5 cm radius acoustic interferometer with variable length between 10 cm and 20 cm.

3.1 Infinite-Length Duct With Uniform ID

We first consider an infinitely long duct with inner radius [r.sub.d]. An acoustic wave entering the duct (point P in the inset in Fig. 1) travels to the right and damps away with no reflection back to the resonator. As stated in the introduction, the input impedance for such a duct is just the characteristic impedance given in Eq. (2). The specific acoustic admittance for the infinite tube is, therefore,

[[bar.y].sub.[infinity]] = [[bar.y].sub.0] = [[[rho]c]/[A.sub.d]][1/[Z.sub.0]] = [square root of [1 + ([gamma] - 1)[F.sub.t]](1 - [F.sub.v])]. (11)

The perturbation of a resonator mode, calculated from Eqs. (9) and (10), shifts the mode's wavenumber (and resonance frequency) by an amount proportional to Re (i[[[[bar.y].sub.[infinity]][r.sub.d.sup.2]]/[a.sup.2]]) and increases the half-width by an amount proportional to Im (i[[[[bar.y].sub.[infinity]][r.sub.d.sup.2]]/[a.sup.2]]). The wide-tube approximation [r.sub.d] [much greater than] [[delta].sub.t] to Eq.(11) is

[[bar.y].sub.[infinity]][approximately equal to]1 - (1 - i)(1 + [square root of Pr] - [gamma])[[[delta].sub.t]/[2[r.sub.d]]] + O[([[delta].sub.t]/[r.sub.d]).sup.2]. (12)

We recommend caution when using Eq. (12) for noble gases because the imaginary part is subject to large errors even when [[[delta].sub.t]/[r.sub.d]] is as small as 0.1. In practice, however, the error in Re([[DELTA]K/[kappa]]) introduced by the wide tube approximation is less than 1 x [10.sup.-6] when [a/[[delta].sub.t]] > 200 for the (0,2) mode of a sphere or [R/[[delta].sub.t]] > 400 for the first longitudinal mode of a cylinder.

Figure 1 shows the calculated admittance of an infinite duct ([r.sub.d] = 0.7 mm) filled with argon at 273 K for pressures of 0.02 MPa (dashed curves) and 0.4 MPa (solid curves). The normalized admittance i [([[r.sub.d]/a]).sup.2] [[bar.y].sub.[infinity]] is plotted as a function of ka . Here, a is either the radius of a spherical resonator or the radius of a cylindrical resonator and is assumed to be 50 mm in either case. The arrows in the figure locate radial modes of a sphere, and the horizontal bar shows the range of ka that will excite longitudinal modes of an interferometer with length L in the range 10 cm < L < 20 cm. We estimate Re([[i[[bar.y].sub.[infinity]][r.sub.d.sup.2]]/[a.sup.2]]) for ka = 1 to be -11.2x[10.sup.-6] and -1.0 x [10.sup.-6] at 0.02 MPa and 0.4 MPa, respectively, whereas Im ([[i[[bar.y].sub.[infinity]][r.sub.d.sup.2]]/[a.sup.2]]) is, respectively, 1.91 x [10.sup.-4] and 1.95 x [10.sup.4]. For the (0,2) mode of a sphere (ka [approximately equal to] 4.49), we estimate Re (i[[bar.y].sub.[infinity]] [r.sub.d.sup.2]/[a.sup.2]) to be -3.6 X [10.sup.-6] and -0.4 X [10.sup.-6] at 0.02 MPa and 0.4 MPa, respectively; Im (i[[bar.y].sub.[infinity]] [r.sub.d.sup.2]/[a.sup.2]) is 1.94 X [10.sup.-4] and 1.94 X [10.sup.-4], respectively.

[FIGURE 1 OMITTED]

3.2 Two-Stage Infinite Tube

We now examine a two-stage infinite tube shown in the inset in Fig. 2. A smaller diameter duct with radius [r.sub.d] and length [l.sub.d] is inserted between the resonator and the infinite duct discussed in Sec. 3.1. The wave present in the short duct will be partially reflected at points P and P' giving rise to standing waves at specific frequencies. Neglecting the effects on the acoustic field of the abrupt transitions at the duct ends, we assume that the pressure and volume velocity are continuous 1-dimentional functions of z. The pressure and volume velocity in the duct are

[p.sub.d] = [p.sub.L][e.sup.[GAMMA]z] + [p.sub.R][e.sup.-[GAMMA]z], [U.sub.d] = - [1/[Z.sub.0]][[p.sub.L][e.sup.[GAMMA]z] - [p.sub.R][e.sup.-[GAMMA]z]] (13)

respectively, and in the infinite tube we have

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] (14)

We match the impedances in the two ducts at point P', i.e., [MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] and then use the impedance at point P, [Z.sub.d] = [([U.sub.d]/[P.sub.d]).sub.[z = 0]], to eliminate [[p.sub.R]/[p.sub.L]] * Rearranging, we obtain

[Z.sub.d] = [Z.sub.0][[[Z'.sub.0] + [Z.sub.0] tanh([GAMMA][l.sub.d])]/[[Z.sub.0] + [Z'.sub.0] tanh([GAMMA][l.sub.d])]]. (15)

Equation (15) has the same form as the equation for a finite-length lossy transmission line (i.e., the small duct) terminated by the impedance [Z'.sub.0]. Derivation of this expression from an equivalent T-network is given in the next section. The specific acoustic admittance at the duct entrance is

[[bar.y].sub.d] = [[bar.y].sub.0][[[Z.sub.0] + [Z'.sub.0] tanh([GAMMA][l.sub.d])]/[[Z'.sub.0] + [Z.sub.0] tanh([GAMMA][l.sub.d])]], (16)

with the definition [[bar.y].sub.o] [equivalent to] [rho]c/([A.sub.d] [Z.sub.0]). Figure 2 shows the specific admittance for the two-stage infinite tube ([r.sub.d] = 0.35 mm, [l.sub.d] = 50 mm) from Eq. (16) scaled by i[([[r.sub.j]/a).sup.2], where a = 50 mm is either the radius of a spherical cavity or the radius of a cylindrical cavity. The acoustic medium is assumed to be argon at 273 K and 0.02 MPa (dashed) and 0.4 MPa (solid). For comparison, the specific admittance of the uniform infinite tube from Eq. (11), scaled by i[([r'.sub.d]/a).sup.2], where [r'.sub.d] = 0.7 mm, is also shown. The peaks in [[bar.y].sub.d] indicate damped resonances. The left-most peak, near ka = 0, is a Helmholtz mode in which gas moves asymmetrically between the resonator and the infinite tube through the small duct. The other peaks are resonances in the small duct. Between the resonances are regions where the admittance is small.

[FIGURE 2 OMITTED]

The length of the short tube in Fig. 2 was chosen such that the modes of the spherical cavity fall in between the modes of the duct where the admittance is near zero. By comparison, the characteristic impedances of the long tube and of the cavity are small compared to the characteristic impedance of the short duct, so the duct itself is nearly a half-wave resonator with resonances when ka [approximately equal to] m [[pi]a/[l.sub.d], with m a positive integer. The anti-resonances (minimum amplitude) occur when ka [approximately equal to] (m+1/2)[pi]a/[l.sub.d]. The low-lying radial modes of a spherical cavity will be close to these anti-resonances if [l.sub.d] = a.

For a cylindrical cavity, the optimum arrangement is different. If [r'.sub.d] > [r.sub.d], as in the inset of Fig. 2, the odd symmetry longitudinal modes can be placed near the anti-resonances if, for example, [l.sub.d] = 1.5 L. However, both the even and odd-symmetry modes cannot be placed near anti-resonances. On the other hand, if we choose [r'.sub.d] < [r.sub.d], then the short duct will be nearly a quarter-wave resonator with anti-resonances when [k.sub.m] = m[[pi]/[l.sub.d]]. If we further choose [l.sub.d] = 1.5 L, the even-symmetry modes of the cavity fall between the modes of the short duct.

3.3 Finite-Length Tube With Uniform ID

The inset in Fig. 3 shows a sketch of a tube (with diameter 2[r.sub.d] and length [l.sub.d]) terminated by an impedance [Z.sub.T]. This arrangement is suitable for a fill duct in which the terminal impedance results from a chamber with volume [V.sub.c], such as a valve. In this case, since the chamber's dimensions are smaller than an acoustic wavelength, [Z.sub.T] will be the impedance of the chamber volume, given by

[FIGURE 3 OMITTED]

[Z.sub.T] = [[[rho][c.sup.2]]/[i[omega][V.sub.c][1 + [1/2](1 - i)([gamma] - 1)[S.sub.c][[delta].sub.t]/[V.sub.c]]]], (17)

where [S.sub.c] is the chamber's surface area. If the duct is open into a pressure vessel, then the termination impedance will likely be dominated by the radiation impedance except perhaps near the resonances of the pressure vessel. Radiation impedance is discussed in Sec. 4. The specific acoustic admittance for this arrangement is

[[bar.y].sub.d] = [[bar.y].sub.0][[[Z.sub.0] + [Z.sub.T] tanh([GAMMA][l.sub.d])]/[[Z.sub.T] + [Z.sub.0] tanh([GAMMA][l.sub.d]). (18)

The normalized specific admittance [[i[[bar.y].sub.d][r.sub.d.sup.2]]/[a.sup.2]] is plotted in Fig. 3 as a function of ka for a tube 3 meters long. The acoustic medium is assumed to be argon at 0.02 MPa and 0.4 MPa. The oscillations in the admittance in Fig. 3 are due to resonances that occur in the tube. The locations of the resonances are sensitive to the termination impedance, however the envelope defined by the peak-to-peak oscillations is determined primarily by the damping in the tube. Therefore, this envelope gives an estimate of the uncertainty in the admittance if the termination volume [V.sub.c] is unknown. The uncertainty in the admittance defined by the envelope is approximately

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] (19)

where the attenuation length [l.sub.a] = 1/Re([GAMMA]) is the characteristic distance that the wave travels in the tube before it damps out (see Sec. 3.5). The attenuation length is about 0.6 m for sound at the frequency of the lowest radial mode (ka = 4.49) in a tube with an inner radius of 0.7 mm filled with argon at 273.16 K and 0.4 MPa pressure. For the dimensions used in Fig. 3 and 0.4 MPa, we estimate [[sigma].sub.[bar.y]] [approximately equal to] [+ or -]5 x [10.sup.-6] and [[sigma].sub.[bar.y]] [approximately equal to] [+ or -] l x[10.sup.-8] at ka = 0.8 and 4.5, respectively.

A special case of an open-ended tuned-length tube is worth considering here. Resonators are usually placed in a pressure vessel to reduce the dimensional changes caused by changes of pressure and to provide thermal isolation. A short open tube can provide a means of changing the gas pressure in the resonator quickly, instead of the much slower method through a long tube. We caution, though, that a duct open to a pressure vessel may cause difficulties if an acoustic mode of the vessel overlaps with a mode of either a spherical or cylindrical cavity.

3.4 Two-Stage Tube With Termination

We now investigate a 2-stage tube in which the opening into the resonator is through a short duct with a smaller diameter, as shown in the inset in Fig. 4. We can use the methods in the previous sections to write the admittance at point P as

[FIGURE 4 OMITTED]

[[bar.y].sub.d] = [[bar.y].sub.0][[[([r'.sub.d]/[r.sub.d]).sup.2][[bar.y]'.sub.d] + [[bar.y].sub.0] tanh([GAMMA][l.sub.d])]/[[[bar.y].sub.0] + [([r'.sub.d]/[r.sub.d]).sup.2][[bar.y]'.sub.d] tanh([GAMMA][l.sub.d])]] (20)

where [[bar.y].sub.d]' is the admittance at point P' from Eq. (18). In Eq. (20), [[bar.y].sub.0] and the unprimed quantities with subscript d refer to the short duct. The results are shown in Fig. 4.

3.5 Design Suitable for Remote Transducers

When tubes are used as acoustic waveguides to transmit sound between the resonator and remote transducers, the perturbation due to the waveguides must be weighed against the signal-to-noise ratio. If not properly addressed, these issues may result in an unacceptably large uncertainty with which the speed of sound or temperature is measured. For example, if a detector microphone is placed at the end of the waveguide, as in the inset of Fig. 3, resonances will occur in the waveguide at specific frequencies due to the impedance mismatch between the duct and the transducer. Weakly-damped resonances in the waveguides may couple to the modes of the resonator causing significant frequency shifts; furthermore, the unwanted resonance response of the tube that may be difficult to deconvolve from the resonator's response. The reflections and the tube resonances can be strongly damped if the waveguide is sufficiently long, but then the attenuation of the desired signal will reduce the signal-to-noise ratio. These and other issues will be discussed in more detail in a forthcoming publication (16). We give the basic concepts below.

A successful design, implemented by Ripple, et al. (9) for the detector and its waveguide, is to mount the detector (T) as a branch with impedance [Z.sub.D] on a long waveguide at an intermediate distance [l.sub.1] from the resonator, as shown in the inset of Fig. 5a. For this split-tube design, the admittance at P is

[FIGURE 5 OMITTED]

[[bar.y].sub.d] = [[bar.y].sub.0] = [[[y.sub.D] + [[bar.y]'.sub.d] + [[bar.y].sub.0]tanh([GAMMA][l.sub.d])]/[[[bar.y].sub.0] + ([y.sub.D] + [[bar.y]'.sub.d])tanh([GAMMA][l.sub.d])]] (21)

where [y.sub.D] [equivalent to] ([[pc/[A.sub.d]]) [Z.sub.D.sup.1], and [[bar.y]'.sub.d] is the admittance at P' given by

[[bar.y]'.sub.d] = [[bar.y].sub.0][[1 + [[bar.y].sub.0]([A.sub.d][Z.sub.T]/[rho]c)tanh([GAMMA][l'.sub.d])]/[[[bar.y].sub.0]([A.sub.d][Z.sub.T]/[rho]c) + tanh([GAMMA][l'.sub.d])]]. (22)

If [l'.sub.d] is sufficiently large, then a wave at P' traveling to the right will be damped out before it reaches the end of the waveguide. The characteristic length for damping is the attenuation length [l.sub.a], the distance a wave must travel for the acoustic pressure to be attenuated to [1/e] of its initial value. Thus, if [l'.sub.d] [much greater than] [l.sub.a] then [[bar.y]'.sub.d] [approximately equal to] [[bar.y].sub.0] from Eq. (22), and [[bar.y].sub.d] in Eq. (21) will be insensitive to [Z.sub.T].

The scaled admittance i[([[r.sub.d]/a]).sup.2] [[bar.y].sub.d] in the limit [l'.sub.d] [right arrow] [infinity] is plotted in Fig. 5a for Ripple's sphere, which had a radius of 9 cm. The transducer Ripple used was a commercially-available micromachined microphone with an estimated internal volume of 8.8 [mm.sup.3] and internal surface area of 60 [mm.sup.3]. The transducer was connected to the waveguide through a short duct with radius [r.sub.n] = 0.5 mm and length [l.sub.n] = 0.6 mm. We approximated the transducer impedance [Z.sub.D] by the sum of the short duct's impedance [Z.sub.neck] [approximately equal to] ([pc/[[pi][r.sub.n.sup.2]]]) [ikl.sub.n]/(1 - [F.sub.vn]), where [F.sub.vn] is the viscous loss function, and the volume's impedance [Z.sub.vol] from Eq. (17) with [V.sub.c] = 8.8 [mm.sup.3] and surface area [S.sub.c] = 60 [mm.sup.2]. The oscillations of the admittance in Fig. 5a indicate resonances in the short section ([l.sub.d] = 0.4 m, [r.sub.d] = 0.7 mm) between the resonator and the transducer. The details of these oscillations are controlled by the reflection coefficient at point P', R = - [[y.sub.D]/([y.sub.D] + 2[[bar.y].sub.0]]The envelope for these oscillations (also shown in Fig. 5a) has the form

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] (23)

The shape of the envelope is determined from two competing phenomena: 1) the magnitude of the reflection coefficient |R| increases as ka (or the frequency) increases, and 2) the attenuation length decreases as ka increases. The attenuation length for a circular duct is

[l.sub.a][equivalent to][1/[Re([[GAMMA].sub.d])]][approximately equal to][[[r.sub.d][square root of 2]]/[[square root of [ka]]([square root of [Pr]] + [gamma] - 1)]][([ca]/[D.sub.t]).sup.[1/2]], (24)

where the approximation is valid for [[delta].sub.1] [much less than] [r.sub.d]. Equation (24) tells us that acoustic waves in a duct travel the furthest at low frequencies and high gas densities, all else being equal. The perturbation from the waveguide and the transducer on the acoustic modes is shown in Fig. 5b. We estimate the perturbation of the (0,2) mode's resonance frequency Re([DELTA][K/k]) to be [+ or -] 0.4 x [10.sup.-6] based on the envelope in Eq. (23).

If both the source and detector are mounted remotely, then the attenuation in both waveguides must be taken into account. An acoustic wave with pressure amplitude [[~.P].sub.s] at the source is attenuated as it propagates a distance [l.sub.s] down the waveguide to the resonator, gets amplified by the resonance quality factor [Q.sub.N], and is again attenuated as it further propagates a distance [l.sub.D] down a similar waveguide to the detector where the acoustic pressure is [[~.p].sub.D]. The ratio of pressures [[[~.p].sub.D]/[[~.p].sub.s]] is proportional to [Q.sub.N] [MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII], which is useful to estimate the source strength needed to achieve a desired signal-noise ratio.

4. Experimental Details

We studied the acoustic propagation between 200 Hz and 10 kHz in 1.4 mm ID tubes using a 3-port acoustic coupler as shown in Fig. 6. The internal chamber of the coupler was conical with a volume of 134 [mm.sup.3] (determined from dimensional measurements). The sound source was a 6 mm diameter condenser microphone cartridge (Bruel & Kjaer (2) 4135) mounted in a flange and placed in one of the ports. The detector was a 3 mm diameter condenser microphone (Bruel & Kjaer 4138) and preamp (Bruel & Kjaer 2669) placed in a second port. The third port held the tube under study. The microphones and the tube were positioned flush with the interior surface of the coupler and were secured with elastomer o-rings and a small amount of grease to fill the crevices. The coupler was operated in ambient air. The temperature of the coupler and the air pressure were continuously recorded. The properties of air from NIST's properties database REFPROP (17) were used to correct for temperature and pressure changes. The admittances of the tubes are determined with a ratio-metric method (described below); therefore, most of the systematic errors due to the properties of air drop out to first order. The tube admittance is a function of [kl.sub.d] = [2[pi]f[l.sub.d]/c]. Since the frequency is known with high accuracy, the uncertainty of the admittance is dominated by the uncertainty in the quantity [[l.sub.d]/c]. The uncertainty in the length measurement u([l.sub.d]) is 0.5 mm, and the relative standard uncertainty of the speed of sound u(c)/c is 0.001.

[FIGURE 6 OMITTED]

The experimental electronics were arranged as shown in Fig. 7. A sinusoidal drive voltage [V.sub.G] at frequency [f.sub.G] from a Hewlett-Packard 3225B function generator was amplified and applied to the source microphone. The applied root mean square (rms) voltage was nominally 20 V, but depended on the frequency. The actual rms drive voltage [V.sub.s] (scaled by a factor of 0.008 with a voltage divider) was measured at each frequency with a digital lock-in amplifier (Stanford Research SR8350). The signal from the detector microphone [V.sub.D](at frequency 2[f.sub.G]) was measured with a second lock-in amplifier. Both the detector and source lock-in amplifiers were referenced to the applied drive voltage to eliminate phase shifts from the external electronics. The detector voltage [V.sub.D] was proportional to [V.sub.s.sup.2], as explained in Appendix A. To remove the frequency dependence of [V.sub.s], we normalized the detector voltage by [(20 V/[V.sub.s]).sup.2]. The acoustic pressure was determined from the expression

[FIGURE 7 OMITTED]

[p.sub.a] = (0.001 Pa/[micro]V)([V.sub.D])[(20 [V/[V.sub.S]]).sup.2]. (25)

The observed root mean squared noise in the acoustic pressure was about u([p.sub.a]) = 0.001 [p.sub.a]. This noise level is consistent with fluctuations in ambient temperature and pressure on the time scale of the measurement at each frequency, since the temperature and pressure of the air in the coupler and the tubes was not controlled.

We studied 9 different lengths all cut from the same tube: 1601.12 mm, 1400.94 mm, 1200.77 mm, 1000.59 mm, 800.01 mm, 599.84 mm, 399.86 mm, 199.48 mm, and 98.51 mm. (These lengths resulted from fits to the admittance data; however, they all were within the 0.5 mm uncertainty of direct measurements of the length using a steel scale.) We determined the inside diameter of a 3 meter length of the tube from measurements of the pressure drop across the tube produced by a known flow rate of nitrogen gas. The rate of flow through the tube was measured with a mass flow transfer standard (DH Instruments, Molbloc-L, calibrated by the NIST Fluid Metrology Group) attached to the upstream end of the tube. The downstream end of the tube was open to the room. The Molbloc's downstream pressure transducer was fitted with a two-way valve that enabled us to measure sequentially the pressure at the junction between the Molbloc and the tube, then ambient room pressure. The difference between the two pressures was a measure of the pressure drop across the long tube. We used three flow rates (nominally 74 [micro]mol/s, 220 [micro]mol/s, and 450 [micro]mol/s) in order to check for nonlinear effects. We analyzed the data with the detailed model for flow in a circular tube described by Berg (18). A small correction due to the increase in kinetic energy at the tube entrance was applied to the flow rate in accordance with Eq. 40 in Ref. (18). This correction increased the flow rate by at most 1 %. Based on these measurements, we determined the tube's inner diameter to be (1.377 [+ or -] 0.005) mm.

The longest tube (1601.12 mm) was used to determine the acoustic source strength [U.sub.0] based on the measured acoustic pressure and the calculated impedances. The source strength was then used to determine the tube impedance from the measured acoustic pressure for the other tube lengths.

The lumped-element model for the acoustic coupler, the source, and the tube is shown in Fig. 8. The acoustic source is modeled as a current source that generates a volume velocity [U.sub.0] [e.sup.i[omega]t]. The acoustic impedance of the coupler volume is denoted [Z.sub.v], and the tube impedance is modeled as a waveguide T-network. The small impedances [Z.sub.end] and [Z.sub.rad] are corrections that account for the imperfect flow fields near the tube end inside the coupler and near the open end, respectively. The detector microphone measures the acoustic pressure [p.sub.a] in the coupler volume as indicated in the figure. If we neglect the small end correction [Z.sub.end] in Fig. 8, the acoustic pressure in the coupler generated by the source is given by [p.sub.a] = [U.sub.0][Z.sub.total], where the total acoustic impedance seen by the source is

[FIGURE 8 OMITTED]

[1/[Z.sub.total]] = [1/[Z.sub.V]] + [1/[Z.sub.tube]]. (26)

In order to include the end effect impedance [Z.sub.end] in Eq. (26), we simply replace [Z.sub.tube] with [Z.sub.tube] + [Z.sub.end].

In the frequency range studied here, the wavelength of sound was always much larger than the coupler's internal dimensions. Under these conditions, the acoustic impedance of a chamber has been shown to be insensitive to the geometry but dependent simply on the volume and surface area. Therefore, the impedance of the coupler volume was assumed to be given by (19)

[Z.sub.V] = [[[rho][c.sup.2]]/[i[omega][V.sub.c]]][1/[1 + (1 - i)([gamma] - 1)[[delta].sub.t][S.sub.c]/(2[V.sub.c])]]. (27)

The input impedance of a tube with radius [r.sub.d] and length [l.sub.d] is given by [see Eq. (4)]

[Z.sub.tube] = [Z.sub.0][[[Z.sub.rad] + [Z.sub.0] tanh([GAMMA][l.sub.d])]/[[Z.sub.0] + [Z.sub.rad] tanh([GAMMA][l.sub.d])]] (28)

where the characteristic impedance [Z.sub.0] and the propagation parameter [GAMMA] include the effects of the thermo-acoustic boundary layer in the tube. The radiation impedance [Z.sub.rad] has the form (for k[r.sub.d] [much less than] 1)

[Z.sub.rad] = [[[rho][omega]]/[A.sub.d]]([[delta].sub.R] + i[[delta].sub.I]) (29)

where [[delta].sub.R] is the orifice resistance parameter and [[delta].sub.I] is the inertial end correction for sound radiating from the end of an unbaffled open tube. We used the results of Levine and Schwinger [20] for an infinitely thin wall tube

[[[delta].sub.I]/[r.sub.d]] = [[epsilon].sub.i0] + [[epsilon].sub.i2][(k[r.sub.d]).sup.2], [[[delta].sub.R]/[r.sub.d]][approximately equal to][1/4]k[r.sub.d] - [1/12][[19/12] - [[gamma].sub.e] - ln(k[r.sub.d])][(k[r.sub.d]).sup.3] (30)

where [[epsilon].sub.i0] = 0.6127, [[epsilon].sub.i2] = -0.1750, and [[gamma].sub.e] is Euler's constant. For convenience, we define the specific acoustic impedance [z.sub.rad] [equivalent to] ([[A.sub.d]/pc])[Z.sub.rad], and the admittances [y.sub.V] [equivalent to] ([pc/[A.sub.d]])([1/[Z.sub.V]]), and [y.sub.tube] = ([pc/[A.sub.d]])([1/[Z.sub.tube]]), and [y.sub.0] = ([pc/[A.sub.d]])([1/[Z.sub.0]]). With these definitions and substitution from Eq. (28), the admittance of the tube is

[y.sub.tube] = [y.sub.0][[1 + [z.sub.rad][y.sub.0]tanh([GAMMA][l.sub.d])]/[[z.sub.rad][y.sub.0] + tanh([GAMMA][l.sub.d])]]. (31)

A plot of [y.sub.v] is shown in Fig. 9.

We attempted to determine the source strength with the tube port plugged, however we were not able to obtain a consistent and repeatable seal around the plug and tubes. Instead, we started with the longest tube (1.6 m) mounted flush with the inner coupler wall, measured the acoustic pressure as a function of frequency, and then cut portions off the tube's free end to change the length without disconnecting the tube from the coupler. In this way, the baseline conditions at the coupler end were undisturbed and could be reliably eliminated.

[FIGURE 9 OMITTED]

Figure 10 shows the measured acoustic pressure with the 1.6 m long tube in place. The source strength [U.sub.0] was determined from the measured acoustic pressure combined with the calculated impedances of the coupler and tube from Eqs. (26)-(28). In terms of admittances, the source strength is

[FIGURE 10 OMITTED]

[U.sub.0] = [[A.sub.d]/[[rho]c]][p.sub.160]([y.sub.V] + [y.sub.160]) (32)

where [p.sub.160] is the measured acoustic pressure, [y.sub.160] is given by Eq. (31) for the 1.6 m tube. The theoretical tube impedance is plotted in Fig. 11, and the source strength deduced using Eq. (32) from the measured acoustic pressure with no adjustable parameters is shown in Fig 12.

[FIGURE 11 OMITTED]

[FIGURE 12 OMITTED]

The simple model for the source given in Appendix A predicts a linear frequency dependence for the source strength with a slope that is consistent with the slope of Re([U.sub.0]) in Fig. 12. At 1000 Hz, the measured source strength was 0.098 [mm.sup.3]/s compared to the predicted value 0.091 [mm.sup.3]/s with no adjustable parameters. The simple model in Appendix A does not predict the observed Im([U.sub.0]), however. Measurements of the acoustic pressure above 10 kHz revealed that the increase in Re(p) with frequency [and therefore the increase in Im([U.sub.0])] is due to the tail of a large resonance at 40 kHz, presumably of the membrane. For all the measurements presented here, the source strength was limited by the microphone's effective volume and membrane tension, but not limited by the impedance of the coupler or the attached tubes. We therefore used the same source strength function for all the tubes in order to deduce the tube impedances.

After shortening the duct by cutting off a section, leaving the attachment to the coupler unaltered, the acoustic pressure as function of frequency was again measured. The admittance of the tube with new length l was determined, with no adjustable parameters, from

[y.sub.l] = ([[[rho]c]/[A.sub.d]])[[U.sub.0]/[p.sub.l]] - [y.sub.V]. (33)

Figure 13 shows the measured acoustic pressure for the 1.4 m length, and the measured tube admittance is plotted in Fig. 14 as a function of frequency. Also plotted in Fig. 14 are the theoretical admittance (solid curve) and the deviations between the measured and calculated values. The root mean square difference between the measured and modeled specific admittances (both real and imaginary parts) over this frequency range was 0.018. The observed noise in the measured acoustic pressure mentioned previously accounts for the scatter in the deviation in Fig. 14. Figures 15 and 16 show similar plots of the acoustic pressure and the measured admittance for the 100 cm long tube.

[FIGURE 13 OMITTED]

[FIGURE 14 OMITTED]

[FIGURE 15 OMITTED]

[FIGURE 16 OMITTED]

We observed the largest systematic deviations between the measured and predicted admittances of the shortest tubes, where the admittance is more sensitive to errors in the length and to the details of the termination impedance. The attenuation length [l.sub.a] = [1/Re([GAMMA])]is a measure of how far the wave propagates down a long tube before damping out. Lower frequency waves travel further than higher frequency waves: [l.sub.a] = 1.4 m at 200 Hz, whereas [l.sub.a] = 0.22 m at 10 kHz. At 200 Hz, the acoustic pressure at the open end of the 20 cm long tube is attenuated by only 13 % of the acoustic pressure in the coupler. Once the wave leaves the open end, the attenuation length is significantly longer.

Our impedance measurements are comparable to the 1982 measurements by Rasmussen (10). He compared the measured and calculated acoustic transfer impedance of a coupler fitted with standard laboratory microphones and two narrow, open-ended tubes. The transfer impedance was measured using a reciprocity technique. Both tubes had a radius of 0.234 mm and a length of 1 m. Rasmussen reported a plot of the change (in dB) of the coupler impedance when the tubes were blocked compared to when the tubes were open. Rasmussen showed that a particular expression for the low-frequency acoustic impedance of a narrow tube (used to correct the coupler impedance for microphone calibrations) was subject to large systematic effects at sufficiently low frequency. Unfortunately, insufficient information was given to directly compare the measured and calculated impedance of a single tube without the coupler.

5. Discussion and Recommendations

Figure 17 shows [[DELTA]K/[kappa]] from Eq. (9) with [z.sub.0n] replaced by ka and [[bar.y].sub.d] due to the single-stage duct (dotted) and two-stage duct (solid) considered in Secs. 3.3 and 3.4 plotted as a continuous function of ka. The predicted perturbations of the radial modes of a spherical cavity (with [alpha] = 5 cm) are found for the values of ka indicated by the arrows. The perturbations of the (0,2) mode from the single-stage duct are (0.20 + 10.7i)x [10.sup.-6] and (0.02 + 10.9i)x [10.sup.-6] at 0.02 MPa and 0.42 MPa, respectively. The perturbations of the (0,2) mode from the two-stage duct are (0.6 + 2.5i)x [10.sup.-6] and (-0.08 + 1.1i)x [10.sup.-6] at 0.02 MPa and 0.42 MPa, respectively. At the higher pressure (0.4 MPa), the modes of the sphere coincide with the anti-resonances of the short duct since we chose the length of the short duct [l.sub.d] = a. The rapid oscillations that occur near and below ka = 1 are due to resonances in the 3 m long duct.

[FIGURE 17 OMITTED]

The perturbations for the longitudinal modes of a (5 cm radius) cylindrical cavity, from Eq. (10) with l[pi] replaced by kL, are obtained by multiplying the vertical axes in Fig. 17 by [(0.2m)/L]. However, the 2-stage arrangement with [r.sub.d] < [r.sub.d]', used to generate the plots, is not optimal for a cylindrical cavity. For the quarter-wave duct, discussed in Sec. 3.2, with [r.sub.d] = 0.7 mm, [r.sub.d]' = 0.35 mm, [l.sub.d] = 1.5L, and L = 2R, the perturbations of the two lowest even-symmetry modes (kR = [pi] and 2[pi]) at 0.02 MPa are (4.1 + 32.7i)x [10.sup.-6] and (0.03 + 16.2i)x [10.sup.-6]; at 0.4 MPa the perturbations are (5.4 + 14.1i)x [10.sup.-6] and (3.5 + 18.4i) x [10.sup.-6], respectively. With this arrangement, two ducts are necessary to flow the test gas through the resonator. We recommend using two cylindrical resonators, one twice as long as the other, to take advantage of the cancellation of the end-plate perturbations at the same frequency. For this reason, the ducts for flowing gas and for remote transducers, if needed, should be placed on the resonator's end plates.

To improve the experimental measurements of the admittance of small-diameter ducts, we recommend the following improvements in decreasing order of importance: 1) controlling the temperature and static pressure of the gas medium to reduce the random noise in the acoustic pressure, 2) devising a method to remove and reattach the tube such that the admittance is reproducible, so that the tube length can be determined more accurately and the coupler's impedance can be measured directly, 3) using argon instead of air as the gas medium to reduce the uncertainty in the gas properties, and 4) blocking the end of the tube opposite the coupler or using another coupler to better define the terminal impedance.

We have examined the perturbations of the modes of an acoustic thermometer caused by circular ducts used either for gas flow or as acoustic waveguides coupled to remote transducers. We calculated the acoustic admittance of circular ducts using a model based on transmission line theory. We used the admittance to calculate the perturbations to the resonance frequencies and half-widths of the modes of spherical and cylindrical acoustic resonators as functions of the duct's radius, length, and the locations of the transducers along the duct's length. We measured the specific acoustic admittances of a series of ducts between 200 Hz and 10 kHz in ambient air and compared the results with theory. For a 1.4 mm inside-diameter, 1.4 m long tube, the root mean square difference between the measured and modeled specific admittances over this frequency range was 0.018 (the magnitude of the specific admittance was nominally one).

6. Appendix A. Condenser Microphone as a Source

A schematic diagram of the Bruel & Kjaer 4135 condenser microphone is shown in Fig. A1. The properties of the 4135 are listed in Table A1. The membrane has a thickness [t.sub.x] and is stretched in tension over an annular insulator (quartz). The membrane flexes with an effective radius [a.sub.x]. The gap [h.sub.x] separates the membrane from a backplate with radius [b.sub.x]. The membrane and the backplate form the two electrodes of a parallel-plate capacitor with capacitance [C.sub.x] = [[[[epsilon].sub.0][pi][b.sub.x.sup.2]]/[h.sub.x]]. When used as a detector, the microphone is biased with a DC voltage of 200 V, and the charging current resulting from motion of the membrane is detected. However, when a condenser microphone is used as a source with sinusoidal drive and no DC bias, the sound waveform it generates is a sinusoid whose frequency is twice the excitation frequency. An advantage to this (2[Florin]) mode of operation is that cross talk between the high voltage excitation and the low voltage of nearby detectors is virtually eliminated.

[FIGURE A1 OMITTED]

A very detailed model of condenser microphones is given in Ref. (21), but is beyond the scope of this article. Our objective in this appendix is to describe the low-frequency behavior of a condenser microphone used as a source. We solve a simplified equation of motion for a membrane under tension whose displacement from equilibrium is y. Additional forces are included to account for the reaction of the gas in the microphone volume and the surrounding environment. Thermoacoustic dissipation is neglected.

If we define y as positive for upward displacement, then a simplified equation of motion is

[[sigma].sub.M][[[[partial derivative].sup.2]y]/[[partial derivative][t.sup.2]]] = T[[nabla].sup.2]y + [p.sub.E] - [DELTA]p. (A1)

The first term on the right hand side of Eq. (Al) is the restoring force per unit area due to the membrane tension, [p.sub.E] is the force per unit area from the applied electric field E

[p.sub.E] = - [1/2][[epsilon].sub.0][E.sup.2] = - [[epsilon].sub.0]/2[h.sub.x.sup.2][V.sup.2], (A2)

and [DELTA]p = [p.sub.a] - [p.sub.x], where [p.sub.a] and [p.sub.x] are the acoustic pressures generated in front of and behind the membrane, respectively. The applied voltage V(t) = [V.sub.s] [MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] is at frequency [[Florin].sub.s], but the electric force on the membrane oscillates at 2[[Florin].sub.s] and has a DC component. Since we are only concerned with the AC response, we replace [V.sup.2] in Eq. (A2) by [V.sub.rms.sup.2] [e.sup.i[omega]t] with [omega] = 2[[omega].sub.s]. The steady-state response of the driven membrane displacement y(t) is also proportional to [e.sup.i[omega]t].

The source strength is defined as the rate of volume displacement averaged over the membrane area

[U.sub.0] = [pi][a.sup.x.sup.2]<y> = i[omega][pi][a.sub.x.sup.2]<y>. (A3)

If the acoustic impedance of the medium in front the transducer is [Z.sub.L] and the impedance of the medium in the space inside the transducer is [Z.sub.x], then we have

[p.sub.a] = [Z.sub.L][U.sub.0] (A4)

and

[p.sub.x] = - [Z.sub.x][U.sub.0]. (A5)

We rewrite Eq. (A1) as

[[nabla].sup.2]y + [K.sup.2]y = [[[[epsilon].sub.0][V.sub.rms.sup.2][e.sup.i[omega]t]]/[2[h.sub.x.sup.2]T]] + [[i[omega][pi][a.sub.x.sup.2]]/T]([Z.sub.L] + [Z.sub.x])<y> (A6)

where [K.sup.2] = [[sigma].sub.M] [[[omega].sup.2]/T]. The steady-state solution for Eq. (A6) can be expanded in terms of the normal modes of a circular membrane with a fixed edge, namely [J.sub.m] ([[[xi].sub.mn]r/[a.sub.x]]) cos (m[theta]), where [J.sub.m] ([[xi].sub.mn]) = 0. Due to the axial symmetry of the drive force, however, only the axially symmetric modes (m = 0) will be considered in the model, i.e.,

y = [[infinity].summation over (n = l)][A.sub.0n]][J.sub.0]([[[[xi].sub.0n]r]/[a.sub.x]])[e.sup.i[omega]t]. (A7)

The coefficients [A.sub.0n] are obtained by substituting (A7) into (A6) and integrating over the membrane area.

For simplicity, we assume the membrane and backplate have the same diameters.

[A.sub.0n] = - [[2[a.sub.x.sup.2]( - [p.sub.E] + [DELTA]p)]/[T([[xi].sub.[0n].sup.2] - [K.sup.2][a.sub.x.sup.2])[[xi].sub.0n][J.sub.1]([[xi].sub.0n])]] (A8)

Equation (A8) predicts the lowest mode of the membrane occurs when [Ka.sub.x] = [[xi].sub.01] [approximately equal to] 2.4048 or about 74 kHz. The average membrane displacement in the low-frequency limit [Ka.sub.x] [much less than] [[xi].sub.01] is

<y> = [[ - [[epsilon].sub.0][V.sub.[rms].sup.2][chi]/(2[h.sub.x.sup.2])]/[1 + i[omega][pi][a.sub.x.sup.2]([Z.sub.c] + [Z.sub.x])[chi]]] (A9)

where we have used the property [[infinity].summation over (n=1)]([1/[[xi].sub.0n.sup.2]]) = 1/32] and identified the membrane compliance [chi] = [[a.sub.x.sup.2]/(8T)]. We can estimate [Z.sub.L] and [Z.sub.x] assuming they represent simple volumes, [V.sub.L] and [V.sub.x], respectively, with the expressions [Z.sub.L] = [p[c.sup.2]/(i[omega][V.sub.L])] and [Z.sub.x] = [p[c.sup.2]/(i[omega][V.sub.x])]. For our application, the volume of the coupler (134 [mm.sup.3]) is very large compared to the transducer's equivalent volume (0.6 [mm.sup.3]), so we can neglect the impedance [Z.sub.L]. This is important because it means that the source strength will not depend strongly on the coupler or the attached tubes.

Finally, the source strength from Eq. (A3) in the low-frequency limit is (neglecting [Z.sub.L])

[U.sub.0] = [[ - i[omega][pi][a.sub.x.sup.2][V.sub.[rms].sup.2][[epsilon].sub.0][chi]/(2[h.sub.x.sup.2])]/[1 + [chi][pi][a.sub.x.sup.2][rho][c.sup.2]/[V.sub.x]]] (A10)

In ambient air ([rho][c.sup.2] = 1.41 x [10.sup.5] Pa) at 1 kHz, Eq. (A10) gives

|[U.sub.0]|[approximately equal to](0.091[mm.sup.3]/s), (A11)

using values from Table Al.

7. References

(1) Michael R. Moldover, Acoustic and microwave resonances applied to measuring the gas constant and the thermodynamic temperature, IEEE Transactions on Instrumentation and Measurement 38, 217 (1989).

(2) M. R. Moldover, S. J. Boyes, C. W. Meyer, and A. R. H. Goodwin, Thermodynamic temperatures of the triple points of mercury and gallium and in the interval 217 K to 303 K, J. Res. Natl. Inst. Stand. Technol. 104, 11 (1999); M. R. Moldover, S, J. Boyes, C. W. Meyer, and A. R. H. Goodwin, Primary Acoustic Thermometry from 217 K to 303 K, TEMPMEKO, Delft, The Netherlands, (1999).

(3) D. C. Ripple, D. R. Defibaugh, M. R. Moldover, and G F. Strouse, Techniques for primary acoustic thermometry to 800 K, in Temperature: Its Measurement and Control in Science and Technology. Proceedings of the 8th International Temperature Symposium 21-24 October 2002, Chicago, 11., vol. 7, ed. By D. C. Ripple (AIP Conf Proc, Melville, New York, 2003), pp. 25-30.

(4) G. F. Strouse, D. R. Defibaugh, M. R. Moldover, and D. C. Ripple, Progress in primary acoustic thermometry at NIST: 273 K to 505 K, in Temperature: Its Measurement and Control in Science and Technology. Proceedings of the 8th International Temperature Symposium 21-24 October 2002, Chicago, II., vol. 7, ed. By D. C. Ripple (AIP Conf Proc., Melville, New York, 2003), pp. 31-36.

(5) D. C. Ripple, G. F. Strouse, and M. R. Moldover, Acoustic thermometry results from 271 K to 552 K, Int. J. Thermophys. 28, 1789-1799(2007).

(6) J. B. Mehl, M. R. Moldover, and L. Pitre, Designing quasi-spherical resonators for acoustic thermometry, Metrologia 41, 295-304 (2004).

(7) G. Benedetto, R. M. Gavioso, R. Spagnolo, P. Marcarino, and A. Merlone, Acoustic measurements of the thermodynamic temperature between the triple point of mercury and 380 K, Metrologia 41, 74-98 (2004).

(8) K. A. Gillis, M. R. Moldover, and A. R. H. Goodwin, Accurate measurements in gases under difficult conditions, Rev. Sci. Instrum. 62, 2213-2217 (1991).

(9) D. R. Ripple, private communication.

(10) K. Rasmussen, Note on the Acoustic Impedance of Narrow Tubes, Acoustica 51, 72-73 (1982).

(11) D. Rodrigues, C. Guianvarc'h, J.-N. Durocher, M. Bruneau, A.-M. Bruneau, A method to measure and interpret input impedance of small acoustic components, J. Sound and Vib. 315,890-910(2008),

(12) K. A. Gillis, J. B. Mehl, and M. R. Moldover, Theory of the Greenspan Viscometer, J. Acoust. Soc. Am. 114, 166 (2003).

(13) I. B. Crandall, Theory of vibrating systems and sound, (Van Nostrand, New York, 1927), pp 229-241.

(14) T. J. Quinn, A. R. Colclough, and T. R. D. Chandler, A new determination of the gas constant by an acoustical method, Philosophical Transactions of the Royal Society of London. Series A: Mathematical and Physical Sciences 283, 367-420 (1976).

(15) P. M. Morse and K. U. Ingard, Theoretical Acoustics (McGraw-Hill, New York, 1968), Sec. 9.4.

(16) K. A. Gillis and M. R. Moldover, Designing ducts for acoustic thermometers, to be published.

(17) NIST Reference Fluid Thermodynamic and Transport Properties Database (REFPROP): Version 8.0.

(18) R. F. Berg, Simple flow meter and viscometer of high accuracy for gases, Metrologia 42, 11-23 (2005).

(19) F. B. Daniels, Acoustic impedance of enclosures, J. Acoust. Soc.Am. 19,569-571 (1947).

(20) H. Levine and J. Schwinger, On the radiation of sound from an unflanged circular pipe, Phys Rev 73, 383 (1948); H. Levine, On the theory of sound reflection in an open-ended cylindrical tube, J. Acoust. Soc. Am. 26, 200-211 (1954).

(21) A. J. Zuckerwar, Principles of Operation of Condenser Microphones, in AIP Handbook of Condenser Microphones, ed. G. S. K. Wong and T. E. W. Embleton (AIP Press, New York, 1995).

(1) current address: Heat Division, National Institute of Metrology (NIM), Beijing 100013, China.

(2) Certain commercial equipment, instruments, or materials are identified in this paper to foster understanding. Such identification does not imply recommendation or endorsement by the National Institute of Standards and Technology, nor does it imply that the materials or equipment identified are necessarily the best available for the purpose.

About the authors: Dr. Keith A. Gillis is a physicist and acoustician in the Fluid Metrology Group in the Process Measurements Division of the NIST Chemical Science and Technology Laboratory. Dr. Hong Lin is in the Heat Division at the National Institute of Metrology (NIM), Beijing, China and was a Guest Researcher at NIST. Dr. Michael R. Moldover is a NIST Fellow and Leader of the Fluid Metrology Group in the Process Measurements Division of the NIST Chemical Science and Technology Laboratory. The National Institute of Standards and Technology is an agency of the U.S. Department of Commerce.

K. A. Gillis, H. Lin, (1) and M. R. Moldover

National Institute of Standards and Technology, Gaithersburg, MD 20899-0001

keith.gillis@nist.gov

linhong@nim.ac.cn

michael.moldover@nist.gov

Accepted: May 19, 2009

Available online: http://www.nist.gov/jres

Key words: acoustic resonator; acoustic thermometry; Boltzmann constant; duct; perturbation; waveguide.

1. Introduction

Acoustic thermometers determine the thermodynamic temperature of dilute, high-purity argon or helium by measuring the acoustic resonance frequencies of a gas-filled cavity (1), (2), (3), (4), (5), (6), (7). Because these resonances have high quality factors, one can measure the frequencies with relative uncertainties of [10.sup.-6] or less. Therefore, uncertainty in determining the thermodynamic temperature results from other factors such as impurities in the gas or imperfections of the model for a particular resonator. The model must account for ducts used to flow gas into and out of the resonant cavity as well as crevices at seams joining sections of the cavity's wall. At high temperatures, the gas under study may be contaminated by outgassing water, hydrogen, etc. Flowing high-purity gas through the resonator via ducts (long, thin tubes) effectively mitigates the problem of outgassing (3), (4), (5). Ducts are also useful as acoustic waveguides to transmit sound between a resonator at high temperature and transducers located near ambient temperature (8), (9). This practice circumvents the problem of manufacturing efficient, stable electroacoustic transducers and cables that function at high temperatures.

In this paper, we calculate the perturbations of the acoustic resonances of gas-filled cavities caused by circular ducts used either for gas flow or as acoustic waveguides coupled to remote transducers. First, we review the well-established model for the acoustic admittance of circular ducts based on transmission line theory (10), (11), (12), (13). We calculate the perturbations to the resonance frequencies and half-widths of the modes of spherical and cylindrical acoustic cavities as functions of the duct's radius, length, and also as a function of the location of the transducers along the duct's length. To verify the model for a circular duct, we measured the complex acoustic admittances of a series of circular tubes as a function of length between 200 Hz and 10 kHz using a three-port acoustic coupler. Over this frequency range, the root mean square difference between the measured and modeled specific admittances of a 1.4 mm ID, 1.4 m long tube was 0.018. We conclude by discussing design considerations for ducts leading to acoustic thermometers.

2. Acoustic Model for Circular Ducts

See Refs. (12) and (13), and references cited therein, for a detailed description of the acoustic model for a duct with a circular cross section. The model is valid for frequencies below the "cutoff frequency" [f.sub.co], the frequency below which only plane waves propagate. If the duct's radius is [r.sub.d] and the speed of sound in the gas is c, then [f.sub.co] [approximately equal to] 0.29 [c/[r.sub.d]] or about 140 kHz for ambient air in a 1.4 mm ID duct. We adopt the [e.sup.i[omega]t] time dependence convention, consistent with Refs. (12) and (13). We restrict the discussion to ducts with length [l.sub.d] [much greater than] [r.sub.d] and thereby neglect the effects of non-planar flow and sharp corners at the ends of the ducts (12). Finally, we assume that the cross-sectional area of the duct [A.sub.d] = [pi][r.sub.d.sup.2] is a small fraction of the resonator's surface area.

The model's central result is that the acoustic pressure [[~.p].sub.[+ or -]] and volume velocity [[~.U].sub.[+ or -]] of damped traveling waves in a duct are plane waves proportional to [e.sup.[[+ or -][GAMMA][z+i][omega]t]], where the propagation constant [GAMMA] is given by

[GAMMA] = [i[omega]/c][square root of [[1 + ([gamma] - 1)[F.sub.t]]/[1 - [F.sub.v]]]]. (1)

Furthermore, the ratios [[~.p].sub.+]/[[~.U].sub.+] and [[~.p].sub.-]/[[~.U].sub.-] define the characteristic impedance [Z.sub.0] of the medium in the duct

[Z.sub.0] = [[rho]c/[A.sub.d]][1/[[square root of (1 - [F.sub.v])[1 + ([gamma] - 1)[F.sub.t]]]]. (2)

The real part of [GAMMA] is a measure of the damping of these traveling waves; [Z.sub.0] determines the phase between [[~.p].sub.[+ or -]] and [[~.U].sub.[+ or -]]. The quantities [F.sub.v] and [F.sub.t] are functions of frequency that account for thermoacoustic dissipation near the duct wall. For a duct with radius [r.sub.d], the thermal loss function is

[F.sub.t][equivalent to][[2[J.sub.1]([[zeta].sub.t])]/[[[zeta].sub.t][J.sub.0]([[zeta].sub.t])]], [[zeta].sub.t] = (1 - i)[r.sub.d]/[[delta].sub.t] (3)

where [J.sub.0] and [J.sub.1] are Bessel functions and [[delta].sub.t]= [square root of [2[[lambda].sub.t]/([rho][C.sub.P][omega])]] is the thermal boundary layer thickness. The viscous loss function [F.sub.v] has the same form as Eq. (3) with [[delta].sub.t] replaced by the viscous boundary layer thickness [[delta].sub.v] = [square root of [2[eta]/[rho][omega]]]. For the gas |properties in these expressions, [rho] is the density, c is the speed of sound, [eta] is the shear viscosity, [[lambda].sub.t] is the thermal conductivity, [C.sub.P] is the isobaric heat capacity per unit mass, [C.sub.v] is the isochoric heat capacity per unit mass, and [gamma] is the heat capacity ratio [C.sub.P]/[C.sub.v]. [F.sub.v] and [F.sub.t] are complex-valued functions of [[delta].sub.v]/[r.sub.d] and [[delta].sub.t]/[r.sub.d], respectively. The length scales [[delta].sub.t] and [[delta].sub.v] are not independent but are related via the Prandtl number Pr = [eta][C.sub.P]/[[lambda].sub.t] by the expression [[delta].sub.v] = [[delta].sub.t] [square root of Pr.]. Since Pr for monatomic gases is a weak function of temperature and pressure, we describe the damping of waves in a duct in terms of [[delta].sub.t]/[r.sub.d] only.

The model for finite-length tubes includes reflections from the ends. The interference between these counter-propagating waves produces standing waves at particular frequencies. Such tube resonances pose a problem if they occur too close in frequency to the cavity's modes used for thermometry and are insufficiently damped. To model a tube with finite length, we use a lumped-element equivalent circuit defined by a T-network as described in Ref. (12). The input impedance of a tube with length [l.sub.d], terminated by an acoustic impedance [Z.sub.T] is

[Z.sub.in] = [Z.sub.0][[[Z.sub.T] + [Z.sub.0]tanh([GAMMA][l.sub.d])]/[[Z.sub.0] + [Z.sub.T]tanh([GAMMA][l.sub.d])]]. (4)

In the following sections, we investigate the perturbation that such a tube or combinations of tubes has on the modes of acoustic resonators.

3. Perturbation of the Modes of an Acoustic Cavity by Ducts

Consider the acoustic modes of a gas in a closed cavity. The acoustic velocity potential [PSI] for the mode N is a solution to the homogeneous Helmholtz Equation

[[nabla].sup.2][[PSI].sub.N] + [[kappa].sub.N.sup.2][[PSI].sub.N] = 0 (5)

and satisfies a set of boundary conditions defined by the properties of the gas and the shape of the cavity. [The "acoustic" fields (velocity, pressure, and temperature) are the propagating solutions of the linearized equations of motion. The diffusing solutions (thermal and shear evanescent waves) are important near the boundary and define the acoustic boundary layers.] We assume here that [[PSI].sub.N] and the eigenvalue [[kappa].sub.N] are known (either from analytical or numerical calculation) and describe the mode of our "unperturbed" resonator. For simplicity, we assume that the mode is non-degenerate. Acoustic resonators typically have holes in the wall to admit/remove gas and ports for acoustic transducers. For measurements at extreme temperatures, it may be necessary to use small tubes (ducts) as acoustic waveguides to convey sound to and from remote transducers. Changes to the cavity wall such as these change the boundary conditions on the acoustic wave in the vicinity and, therefore, slightly alter [[PSI].sub.N] and [[kappa].sub.N]. For metrology applications, these perturbations must be quantified with high accuracy.

We focus on spherical, quasi-spherical, and cylindrical cavities. Each shape has advantages. Spherical cavities are characterized by a single length (the radius). Quasi-spherical cavities are nearly spherical cavities with a known shape perturbation that splits the degeneracy of the microwave modes and the non-radial acoustic modes of a perfect sphere. The radially-symmetric modes of a gas-filled quasi-spherical cavity are affected by the shape perturbation only in the second order. Thus, the first-order results in this paper for spherical cavities apply to quasi-spherical cavities as well. Since the wave velocity of a radial mode in a spherical cavity is normal to the cavity's wall, there is no viscous boundary layer dissipation. Therefore, the quality factors (Q) of radial modes in spherical cavities are substantially higher than the Qs of modes in nonspherical cavities with the same volume.

The modes of a fixed-length cylindrical cavity are determined by two parameters: its radius and its length. An acoustic interferometer is a cylindrical resonator in which one end is a moveable piston, so that the cavity's length is variable. The interferometer is operated at a fixed frequency while the length is varied through a succession of resonances (14). With the interferometer, the speed of sound is determined not from an absolute length but from the measured displacement of the piston between successive resonances. Furthermore, since the measurements are at fixed frequency, the perturbations from the end plates cancel out to first order. An alternative to the interferometer, which avoids the complications of a moveable piston, uses two cylindrical resonators in which the length of one is twice the length of the other. The modes of the shorter cavity occur at the same frequencies as the even-order modes of the longer cavity. The combined measurements from both cavities at the same frequencies also have the advantage that the perturbations from the endplates cancel to first order.

The theory for calculating boundary perturbations has been published elsewhere (15). From first-order perturbation theory, the shift of the eigenvalue [[kappa].sub.N] due to a non-uniform surface admittance is

[[[[DELTA][K.sub.N]]/[[kappa].sub.N]]][approximately equal to][[i[omega]]/[2c[[kappa].sub.N.sup.2]]][[[[integral].sub.S][[PSI].sub.N.sup.2]y([omega], [r.sub.S])dS]/[[[integral].sub.V][[PSI].sub.N.sup.2]dV]] (6)

where y([omega], [r.sub.s]) is the specific acoustic admittance at point [r.sub.s] on the boundary. In terms of the acoustic velocity [[~.u].sub.ac] and the acoustic pressure [~.p], y([omega], [r.sub.s]) is defined as

y([omega], [r.sub.S]) = [[[rho]c[^.n] * [[~.u].sub.ac]([omega], [r.sub.S])]/[[~.p]([omega], [r.sub.S])]] (7)

where [^.n] is the outward pointing normal unit vector at [r.sub.s].

For the ideal resonator, the walls are assumed to have zero admittance. The presence of the duct changes the shape from the perfect resonator and therefore changes the mode wavenumbers, because the acoustic wave propagates into the duct and may be partially reflected back into the resonator. Furthermore, a lossy duct causes additional thermoacoustic dissipation. Thus, the acoustic wave in the resonator locally "feels" a larger admittance at the entrance to the duct than at the cavity's wall. If the duct's diameter is small compared to the cavity's diameter, then the long-wavelength acoustic waves will not vary appreciably over the cross section of the duct; therefore, we can expand [PSI] about the duct position [r.sub.d] and use the average admittance of the duct over its cross section [[bar.y].sub.d]. The leading term in the approximation to the surface integral in Eq. (6) is

[[integral].sub.S][[[[PSI].sub.N]([r.sub.S])].sup.2]y([omega], [r.sub.S])dS[approximately equal to][[bar.y].sub.d]([omega])[[[[PSI].sub.N]([r.sub.d])].sup.2][A.sub.d]. (8)

The wavenumber for the nth radial mode of a spherical resonator with radius a is changed by a fractional amount, from Eq. (6),

[[[DELTA][K.sub.n]]/[[kappa].sub.n]][approximately equal to][[i[[bar.y].sub.d][A.sub.d]]/[4[pi][a.sup.2][z.sub.0n]]], (9)

where [z.sub.0n] denotes the nth zero of [dj.sub.0](x)/dx, n = 2, 3, 4, ... Because of the spherical symmetry, the perturbation of the radial-mode wavenumbers does not depend on the location of the duct.

For the lth longitudinal mode of a cylindrical resonator with radius R and length L, Eq. (6) becomes

[[[DELTA][K.sub.l]]/[[kappa].sub.l]][approximately equal to][[i[[bar.y].sub.d][A.sub.d]]/[l[[pi].sup.2][R.sup.2]]][cos.sup.2](l[pi][z.sub.d]/L) (10)

where 0 [less than or equal to] [z.sub.d] [less than or equal to] L is the axial location of the duct and l = 1, 2, 3, ... The first-order perturbation of longitudinal modes when the duct mounted on an endplate ([z.sub.d] = 0, L) is independent of where on the endplate the duct is located. The position of the duct [z.sub.d] must be chosen carefully based on the duct's purpose. For ducts used with remote transducers, there is a competition between the desire for small perturbations and the desire for efficient coupling with the acoustic modes of the resonator. The perturbation will be smallest when the duct is placed near a pressure node, i.e., 2l[z.sub.d]/L = 1, 3, 5, ...; however, at this location the coupling between the mode and the transducers is least efficient. The perturbation will be largest when the duct is placed near a pressure anti-node, i.e., 2l[z.sub.d]/L = 0, 2, 4, 6, ... and the coupling will be most efficient. Node placement is a good choice if the duct's purpose is to flow gas into and out of the resonator; however, it may be a bad choice if the duct is a wave-guide leading to a remote transducer. When the cavity's length is fixed, the locations of the pressure nodes and anti-nodes on the cylindrical wall depend on the mode. With an interferometer, the cavity length is varied between two extremes [L.sub.min] and [L.sub.max], and the frequency (and therefore wavelength) is held constant. Therefore, the locations of the pressure nodes and anti-nodes are fixed in space. This feature of the interferometer suggests that an arrangement where the acoustic waveguides are located on the fixed endplate to maximize the coupling to all the modes, and the fill ducts are attached to the side of the resonator at [z.sub.d] = [L.sub.min]/2 at the pressure node. The disadvantage to this arrangement is that it only works for the odd-symmetry modes, which are susceptible to the effects of center-of-mass motion. A better method is to locate the fill ducts and the waveguides on the endplates, study only the even-symmetry modes (to avoid center-of-mass motion), and rely on the cancellation of the first-order perturbations.

In the following sections, we model the acoustic admittance of several duct geometries. Then we estimate the perturbations due to the duct on the radial modes of a 5 cm radius spherical resonator and on the longitudinal modes of a 5 cm radius acoustic interferometer with variable length between 10 cm and 20 cm.

3.1 Infinite-Length Duct With Uniform ID

We first consider an infinitely long duct with inner radius [r.sub.d]. An acoustic wave entering the duct (point P in the inset in Fig. 1) travels to the right and damps away with no reflection back to the resonator. As stated in the introduction, the input impedance for such a duct is just the characteristic impedance given in Eq. (2). The specific acoustic admittance for the infinite tube is, therefore,

[[bar.y].sub.[infinity]] = [[bar.y].sub.0] = [[[rho]c]/[A.sub.d]][1/[Z.sub.0]] = [square root of [1 + ([gamma] - 1)[F.sub.t]](1 - [F.sub.v])]. (11)

The perturbation of a resonator mode, calculated from Eqs. (9) and (10), shifts the mode's wavenumber (and resonance frequency) by an amount proportional to Re (i[[[[bar.y].sub.[infinity]][r.sub.d.sup.2]]/[a.sup.2]]) and increases the half-width by an amount proportional to Im (i[[[[bar.y].sub.[infinity]][r.sub.d.sup.2]]/[a.sup.2]]). The wide-tube approximation [r.sub.d] [much greater than] [[delta].sub.t] to Eq.(11) is

[[bar.y].sub.[infinity]][approximately equal to]1 - (1 - i)(1 + [square root of Pr] - [gamma])[[[delta].sub.t]/[2[r.sub.d]]] + O[([[delta].sub.t]/[r.sub.d]).sup.2]. (12)

We recommend caution when using Eq. (12) for noble gases because the imaginary part is subject to large errors even when [[[delta].sub.t]/[r.sub.d]] is as small as 0.1. In practice, however, the error in Re([[DELTA]K/[kappa]]) introduced by the wide tube approximation is less than 1 x [10.sup.-6] when [a/[[delta].sub.t]] > 200 for the (0,2) mode of a sphere or [R/[[delta].sub.t]] > 400 for the first longitudinal mode of a cylinder.

Figure 1 shows the calculated admittance of an infinite duct ([r.sub.d] = 0.7 mm) filled with argon at 273 K for pressures of 0.02 MPa (dashed curves) and 0.4 MPa (solid curves). The normalized admittance i [([[r.sub.d]/a]).sup.2] [[bar.y].sub.[infinity]] is plotted as a function of ka . Here, a is either the radius of a spherical resonator or the radius of a cylindrical resonator and is assumed to be 50 mm in either case. The arrows in the figure locate radial modes of a sphere, and the horizontal bar shows the range of ka that will excite longitudinal modes of an interferometer with length L in the range 10 cm < L < 20 cm. We estimate Re([[i[[bar.y].sub.[infinity]][r.sub.d.sup.2]]/[a.sup.2]]) for ka = 1 to be -11.2x[10.sup.-6] and -1.0 x [10.sup.-6] at 0.02 MPa and 0.4 MPa, respectively, whereas Im ([[i[[bar.y].sub.[infinity]][r.sub.d.sup.2]]/[a.sup.2]]) is, respectively, 1.91 x [10.sup.-4] and 1.95 x [10.sup.4]. For the (0,2) mode of a sphere (ka [approximately equal to] 4.49), we estimate Re (i[[bar.y].sub.[infinity]] [r.sub.d.sup.2]/[a.sup.2]) to be -3.6 X [10.sup.-6] and -0.4 X [10.sup.-6] at 0.02 MPa and 0.4 MPa, respectively; Im (i[[bar.y].sub.[infinity]] [r.sub.d.sup.2]/[a.sup.2]) is 1.94 X [10.sup.-4] and 1.94 X [10.sup.-4], respectively.

[FIGURE 1 OMITTED]

3.2 Two-Stage Infinite Tube

We now examine a two-stage infinite tube shown in the inset in Fig. 2. A smaller diameter duct with radius [r.sub.d] and length [l.sub.d] is inserted between the resonator and the infinite duct discussed in Sec. 3.1. The wave present in the short duct will be partially reflected at points P and P' giving rise to standing waves at specific frequencies. Neglecting the effects on the acoustic field of the abrupt transitions at the duct ends, we assume that the pressure and volume velocity are continuous 1-dimentional functions of z. The pressure and volume velocity in the duct are

[p.sub.d] = [p.sub.L][e.sup.[GAMMA]z] + [p.sub.R][e.sup.-[GAMMA]z], [U.sub.d] = - [1/[Z.sub.0]][[p.sub.L][e.sup.[GAMMA]z] - [p.sub.R][e.sup.-[GAMMA]z]] (13)

respectively, and in the infinite tube we have

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] (14)

We match the impedances in the two ducts at point P', i.e., [MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] and then use the impedance at point P, [Z.sub.d] = [([U.sub.d]/[P.sub.d]).sub.[z = 0]], to eliminate [[p.sub.R]/[p.sub.L]] * Rearranging, we obtain

[Z.sub.d] = [Z.sub.0][[[Z'.sub.0] + [Z.sub.0] tanh([GAMMA][l.sub.d])]/[[Z.sub.0] + [Z'.sub.0] tanh([GAMMA][l.sub.d])]]. (15)

Equation (15) has the same form as the equation for a finite-length lossy transmission line (i.e., the small duct) terminated by the impedance [Z'.sub.0]. Derivation of this expression from an equivalent T-network is given in the next section. The specific acoustic admittance at the duct entrance is

[[bar.y].sub.d] = [[bar.y].sub.0][[[Z.sub.0] + [Z'.sub.0] tanh([GAMMA][l.sub.d])]/[[Z'.sub.0] + [Z.sub.0] tanh([GAMMA][l.sub.d])]], (16)

with the definition [[bar.y].sub.o] [equivalent to] [rho]c/([A.sub.d] [Z.sub.0]). Figure 2 shows the specific admittance for the two-stage infinite tube ([r.sub.d] = 0.35 mm, [l.sub.d] = 50 mm) from Eq. (16) scaled by i[([[r.sub.j]/a).sup.2], where a = 50 mm is either the radius of a spherical cavity or the radius of a cylindrical cavity. The acoustic medium is assumed to be argon at 273 K and 0.02 MPa (dashed) and 0.4 MPa (solid). For comparison, the specific admittance of the uniform infinite tube from Eq. (11), scaled by i[([r'.sub.d]/a).sup.2], where [r'.sub.d] = 0.7 mm, is also shown. The peaks in [[bar.y].sub.d] indicate damped resonances. The left-most peak, near ka = 0, is a Helmholtz mode in which gas moves asymmetrically between the resonator and the infinite tube through the small duct. The other peaks are resonances in the small duct. Between the resonances are regions where the admittance is small.

[FIGURE 2 OMITTED]

The length of the short tube in Fig. 2 was chosen such that the modes of the spherical cavity fall in between the modes of the duct where the admittance is near zero. By comparison, the characteristic impedances of the long tube and of the cavity are small compared to the characteristic impedance of the short duct, so the duct itself is nearly a half-wave resonator with resonances when ka [approximately equal to] m [[pi]a/[l.sub.d], with m a positive integer. The anti-resonances (minimum amplitude) occur when ka [approximately equal to] (m+1/2)[pi]a/[l.sub.d]. The low-lying radial modes of a spherical cavity will be close to these anti-resonances if [l.sub.d] = a.

For a cylindrical cavity, the optimum arrangement is different. If [r'.sub.d] > [r.sub.d], as in the inset of Fig. 2, the odd symmetry longitudinal modes can be placed near the anti-resonances if, for example, [l.sub.d] = 1.5 L. However, both the even and odd-symmetry modes cannot be placed near anti-resonances. On the other hand, if we choose [r'.sub.d] < [r.sub.d], then the short duct will be nearly a quarter-wave resonator with anti-resonances when [k.sub.m] = m[[pi]/[l.sub.d]]. If we further choose [l.sub.d] = 1.5 L, the even-symmetry modes of the cavity fall between the modes of the short duct.

3.3 Finite-Length Tube With Uniform ID

The inset in Fig. 3 shows a sketch of a tube (with diameter 2[r.sub.d] and length [l.sub.d]) terminated by an impedance [Z.sub.T]. This arrangement is suitable for a fill duct in which the terminal impedance results from a chamber with volume [V.sub.c], such as a valve. In this case, since the chamber's dimensions are smaller than an acoustic wavelength, [Z.sub.T] will be the impedance of the chamber volume, given by

[FIGURE 3 OMITTED]

[Z.sub.T] = [[[rho][c.sup.2]]/[i[omega][V.sub.c][1 + [1/2](1 - i)([gamma] - 1)[S.sub.c][[delta].sub.t]/[V.sub.c]]]], (17)

where [S.sub.c] is the chamber's surface area. If the duct is open into a pressure vessel, then the termination impedance will likely be dominated by the radiation impedance except perhaps near the resonances of the pressure vessel. Radiation impedance is discussed in Sec. 4. The specific acoustic admittance for this arrangement is

[[bar.y].sub.d] = [[bar.y].sub.0][[[Z.sub.0] + [Z.sub.T] tanh([GAMMA][l.sub.d])]/[[Z.sub.T] + [Z.sub.0] tanh([GAMMA][l.sub.d]). (18)

The normalized specific admittance [[i[[bar.y].sub.d][r.sub.d.sup.2]]/[a.sup.2]] is plotted in Fig. 3 as a function of ka for a tube 3 meters long. The acoustic medium is assumed to be argon at 0.02 MPa and 0.4 MPa. The oscillations in the admittance in Fig. 3 are due to resonances that occur in the tube. The locations of the resonances are sensitive to the termination impedance, however the envelope defined by the peak-to-peak oscillations is determined primarily by the damping in the tube. Therefore, this envelope gives an estimate of the uncertainty in the admittance if the termination volume [V.sub.c] is unknown. The uncertainty in the admittance defined by the envelope is approximately

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] (19)

where the attenuation length [l.sub.a] = 1/Re([GAMMA]) is the characteristic distance that the wave travels in the tube before it damps out (see Sec. 3.5). The attenuation length is about 0.6 m for sound at the frequency of the lowest radial mode (ka = 4.49) in a tube with an inner radius of 0.7 mm filled with argon at 273.16 K and 0.4 MPa pressure. For the dimensions used in Fig. 3 and 0.4 MPa, we estimate [[sigma].sub.[bar.y]] [approximately equal to] [+ or -]5 x [10.sup.-6] and [[sigma].sub.[bar.y]] [approximately equal to] [+ or -] l x[10.sup.-8] at ka = 0.8 and 4.5, respectively.

A special case of an open-ended tuned-length tube is worth considering here. Resonators are usually placed in a pressure vessel to reduce the dimensional changes caused by changes of pressure and to provide thermal isolation. A short open tube can provide a means of changing the gas pressure in the resonator quickly, instead of the much slower method through a long tube. We caution, though, that a duct open to a pressure vessel may cause difficulties if an acoustic mode of the vessel overlaps with a mode of either a spherical or cylindrical cavity.

3.4 Two-Stage Tube With Termination

We now investigate a 2-stage tube in which the opening into the resonator is through a short duct with a smaller diameter, as shown in the inset in Fig. 4. We can use the methods in the previous sections to write the admittance at point P as

[FIGURE 4 OMITTED]

[[bar.y].sub.d] = [[bar.y].sub.0][[[([r'.sub.d]/[r.sub.d]).sup.2][[bar.y]'.sub.d] + [[bar.y].sub.0] tanh([GAMMA][l.sub.d])]/[[[bar.y].sub.0] + [([r'.sub.d]/[r.sub.d]).sup.2][[bar.y]'.sub.d] tanh([GAMMA][l.sub.d])]] (20)

where [[bar.y].sub.d]' is the admittance at point P' from Eq. (18). In Eq. (20), [[bar.y].sub.0] and the unprimed quantities with subscript d refer to the short duct. The results are shown in Fig. 4.

3.5 Design Suitable for Remote Transducers

When tubes are used as acoustic waveguides to transmit sound between the resonator and remote transducers, the perturbation due to the waveguides must be weighed against the signal-to-noise ratio. If not properly addressed, these issues may result in an unacceptably large uncertainty with which the speed of sound or temperature is measured. For example, if a detector microphone is placed at the end of the waveguide, as in the inset of Fig. 3, resonances will occur in the waveguide at specific frequencies due to the impedance mismatch between the duct and the transducer. Weakly-damped resonances in the waveguides may couple to the modes of the resonator causing significant frequency shifts; furthermore, the unwanted resonance response of the tube that may be difficult to deconvolve from the resonator's response. The reflections and the tube resonances can be strongly damped if the waveguide is sufficiently long, but then the attenuation of the desired signal will reduce the signal-to-noise ratio. These and other issues will be discussed in more detail in a forthcoming publication (16). We give the basic concepts below.

A successful design, implemented by Ripple, et al. (9) for the detector and its waveguide, is to mount the detector (T) as a branch with impedance [Z.sub.D] on a long waveguide at an intermediate distance [l.sub.1] from the resonator, as shown in the inset of Fig. 5a. For this split-tube design, the admittance at P is

[FIGURE 5 OMITTED]

[[bar.y].sub.d] = [[bar.y].sub.0] = [[[y.sub.D] + [[bar.y]'.sub.d] + [[bar.y].sub.0]tanh([GAMMA][l.sub.d])]/[[[bar.y].sub.0] + ([y.sub.D] + [[bar.y]'.sub.d])tanh([GAMMA][l.sub.d])]] (21)

where [y.sub.D] [equivalent to] ([[pc/[A.sub.d]]) [Z.sub.D.sup.1], and [[bar.y]'.sub.d] is the admittance at P' given by

[[bar.y]'.sub.d] = [[bar.y].sub.0][[1 + [[bar.y].sub.0]([A.sub.d][Z.sub.T]/[rho]c)tanh([GAMMA][l'.sub.d])]/[[[bar.y].sub.0]([A.sub.d][Z.sub.T]/[rho]c) + tanh([GAMMA][l'.sub.d])]]. (22)

If [l'.sub.d] is sufficiently large, then a wave at P' traveling to the right will be damped out before it reaches the end of the waveguide. The characteristic length for damping is the attenuation length [l.sub.a], the distance a wave must travel for the acoustic pressure to be attenuated to [1/e] of its initial value. Thus, if [l'.sub.d] [much greater than] [l.sub.a] then [[bar.y]'.sub.d] [approximately equal to] [[bar.y].sub.0] from Eq. (22), and [[bar.y].sub.d] in Eq. (21) will be insensitive to [Z.sub.T].

The scaled admittance i[([[r.sub.d]/a]).sup.2] [[bar.y].sub.d] in the limit [l'.sub.d] [right arrow] [infinity] is plotted in Fig. 5a for Ripple's sphere, which had a radius of 9 cm. The transducer Ripple used was a commercially-available micromachined microphone with an estimated internal volume of 8.8 [mm.sup.3] and internal surface area of 60 [mm.sup.3]. The transducer was connected to the waveguide through a short duct with radius [r.sub.n] = 0.5 mm and length [l.sub.n] = 0.6 mm. We approximated the transducer impedance [Z.sub.D] by the sum of the short duct's impedance [Z.sub.neck] [approximately equal to] ([pc/[[pi][r.sub.n.sup.2]]]) [ikl.sub.n]/(1 - [F.sub.vn]), where [F.sub.vn] is the viscous loss function, and the volume's impedance [Z.sub.vol] from Eq. (17) with [V.sub.c] = 8.8 [mm.sup.3] and surface area [S.sub.c] = 60 [mm.sup.2]. The oscillations of the admittance in Fig. 5a indicate resonances in the short section ([l.sub.d] = 0.4 m, [r.sub.d] = 0.7 mm) between the resonator and the transducer. The details of these oscillations are controlled by the reflection coefficient at point P', R = - [[y.sub.D]/([y.sub.D] + 2[[bar.y].sub.0]]The envelope for these oscillations (also shown in Fig. 5a) has the form

[MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] (23)

The shape of the envelope is determined from two competing phenomena: 1) the magnitude of the reflection coefficient |R| increases as ka (or the frequency) increases, and 2) the attenuation length decreases as ka increases. The attenuation length for a circular duct is

[l.sub.a][equivalent to][1/[Re([[GAMMA].sub.d])]][approximately equal to][[[r.sub.d][square root of 2]]/[[square root of [ka]]([square root of [Pr]] + [gamma] - 1)]][([ca]/[D.sub.t]).sup.[1/2]], (24)

where the approximation is valid for [[delta].sub.1] [much less than] [r.sub.d]. Equation (24) tells us that acoustic waves in a duct travel the furthest at low frequencies and high gas densities, all else being equal. The perturbation from the waveguide and the transducer on the acoustic modes is shown in Fig. 5b. We estimate the perturbation of the (0,2) mode's resonance frequency Re([DELTA][K/k]) to be [+ or -] 0.4 x [10.sup.-6] based on the envelope in Eq. (23).

If both the source and detector are mounted remotely, then the attenuation in both waveguides must be taken into account. An acoustic wave with pressure amplitude [[~.P].sub.s] at the source is attenuated as it propagates a distance [l.sub.s] down the waveguide to the resonator, gets amplified by the resonance quality factor [Q.sub.N], and is again attenuated as it further propagates a distance [l.sub.D] down a similar waveguide to the detector where the acoustic pressure is [[~.p].sub.D]. The ratio of pressures [[[~.p].sub.D]/[[~.p].sub.s]] is proportional to [Q.sub.N] [MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII], which is useful to estimate the source strength needed to achieve a desired signal-noise ratio.

4. Experimental Details

We studied the acoustic propagation between 200 Hz and 10 kHz in 1.4 mm ID tubes using a 3-port acoustic coupler as shown in Fig. 6. The internal chamber of the coupler was conical with a volume of 134 [mm.sup.3] (determined from dimensional measurements). The sound source was a 6 mm diameter condenser microphone cartridge (Bruel & Kjaer (2) 4135) mounted in a flange and placed in one of the ports. The detector was a 3 mm diameter condenser microphone (Bruel & Kjaer 4138) and preamp (Bruel & Kjaer 2669) placed in a second port. The third port held the tube under study. The microphones and the tube were positioned flush with the interior surface of the coupler and were secured with elastomer o-rings and a small amount of grease to fill the crevices. The coupler was operated in ambient air. The temperature of the coupler and the air pressure were continuously recorded. The properties of air from NIST's properties database REFPROP (17) were used to correct for temperature and pressure changes. The admittances of the tubes are determined with a ratio-metric method (described below); therefore, most of the systematic errors due to the properties of air drop out to first order. The tube admittance is a function of [kl.sub.d] = [2[pi]f[l.sub.d]/c]. Since the frequency is known with high accuracy, the uncertainty of the admittance is dominated by the uncertainty in the quantity [[l.sub.d]/c]. The uncertainty in the length measurement u([l.sub.d]) is 0.5 mm, and the relative standard uncertainty of the speed of sound u(c)/c is 0.001.

[FIGURE 6 OMITTED]

The experimental electronics were arranged as shown in Fig. 7. A sinusoidal drive voltage [V.sub.G] at frequency [f.sub.G] from a Hewlett-Packard 3225B function generator was amplified and applied to the source microphone. The applied root mean square (rms) voltage was nominally 20 V, but depended on the frequency. The actual rms drive voltage [V.sub.s] (scaled by a factor of 0.008 with a voltage divider) was measured at each frequency with a digital lock-in amplifier (Stanford Research SR8350). The signal from the detector microphone [V.sub.D](at frequency 2[f.sub.G]) was measured with a second lock-in amplifier. Both the detector and source lock-in amplifiers were referenced to the applied drive voltage to eliminate phase shifts from the external electronics. The detector voltage [V.sub.D] was proportional to [V.sub.s.sup.2], as explained in Appendix A. To remove the frequency dependence of [V.sub.s], we normalized the detector voltage by [(20 V/[V.sub.s]).sup.2]. The acoustic pressure was determined from the expression

[FIGURE 7 OMITTED]

[p.sub.a] = (0.001 Pa/[micro]V)([V.sub.D])[(20 [V/[V.sub.S]]).sup.2]. (25)

The observed root mean squared noise in the acoustic pressure was about u([p.sub.a]) = 0.001 [p.sub.a]. This noise level is consistent with fluctuations in ambient temperature and pressure on the time scale of the measurement at each frequency, since the temperature and pressure of the air in the coupler and the tubes was not controlled.

We studied 9 different lengths all cut from the same tube: 1601.12 mm, 1400.94 mm, 1200.77 mm, 1000.59 mm, 800.01 mm, 599.84 mm, 399.86 mm, 199.48 mm, and 98.51 mm. (These lengths resulted from fits to the admittance data; however, they all were within the 0.5 mm uncertainty of direct measurements of the length using a steel scale.) We determined the inside diameter of a 3 meter length of the tube from measurements of the pressure drop across the tube produced by a known flow rate of nitrogen gas. The rate of flow through the tube was measured with a mass flow transfer standard (DH Instruments, Molbloc-L, calibrated by the NIST Fluid Metrology Group) attached to the upstream end of the tube. The downstream end of the tube was open to the room. The Molbloc's downstream pressure transducer was fitted with a two-way valve that enabled us to measure sequentially the pressure at the junction between the Molbloc and the tube, then ambient room pressure. The difference between the two pressures was a measure of the pressure drop across the long tube. We used three flow rates (nominally 74 [micro]mol/s, 220 [micro]mol/s, and 450 [micro]mol/s) in order to check for nonlinear effects. We analyzed the data with the detailed model for flow in a circular tube described by Berg (18). A small correction due to the increase in kinetic energy at the tube entrance was applied to the flow rate in accordance with Eq. 40 in Ref. (18). This correction increased the flow rate by at most 1 %. Based on these measurements, we determined the tube's inner diameter to be (1.377 [+ or -] 0.005) mm.

The longest tube (1601.12 mm) was used to determine the acoustic source strength [U.sub.0] based on the measured acoustic pressure and the calculated impedances. The source strength was then used to determine the tube impedance from the measured acoustic pressure for the other tube lengths.

The lumped-element model for the acoustic coupler, the source, and the tube is shown in Fig. 8. The acoustic source is modeled as a current source that generates a volume velocity [U.sub.0] [e.sup.i[omega]t]. The acoustic impedance of the coupler volume is denoted [Z.sub.v], and the tube impedance is modeled as a waveguide T-network. The small impedances [Z.sub.end] and [Z.sub.rad] are corrections that account for the imperfect flow fields near the tube end inside the coupler and near the open end, respectively. The detector microphone measures the acoustic pressure [p.sub.a] in the coupler volume as indicated in the figure. If we neglect the small end correction [Z.sub.end] in Fig. 8, the acoustic pressure in the coupler generated by the source is given by [p.sub.a] = [U.sub.0][Z.sub.total], where the total acoustic impedance seen by the source is

[FIGURE 8 OMITTED]

[1/[Z.sub.total]] = [1/[Z.sub.V]] + [1/[Z.sub.tube]]. (26)

In order to include the end effect impedance [Z.sub.end] in Eq. (26), we simply replace [Z.sub.tube] with [Z.sub.tube] + [Z.sub.end].

In the frequency range studied here, the wavelength of sound was always much larger than the coupler's internal dimensions. Under these conditions, the acoustic impedance of a chamber has been shown to be insensitive to the geometry but dependent simply on the volume and surface area. Therefore, the impedance of the coupler volume was assumed to be given by (19)

[Z.sub.V] = [[[rho][c.sup.2]]/[i[omega][V.sub.c]]][1/[1 + (1 - i)([gamma] - 1)[[delta].sub.t][S.sub.c]/(2[V.sub.c])]]. (27)

The input impedance of a tube with radius [r.sub.d] and length [l.sub.d] is given by [see Eq. (4)]

[Z.sub.tube] = [Z.sub.0][[[Z.sub.rad] + [Z.sub.0] tanh([GAMMA][l.sub.d])]/[[Z.sub.0] + [Z.sub.rad] tanh([GAMMA][l.sub.d])]] (28)

where the characteristic impedance [Z.sub.0] and the propagation parameter [GAMMA] include the effects of the thermo-acoustic boundary layer in the tube. The radiation impedance [Z.sub.rad] has the form (for k[r.sub.d] [much less than] 1)

[Z.sub.rad] = [[[rho][omega]]/[A.sub.d]]([[delta].sub.R] + i[[delta].sub.I]) (29)

where [[delta].sub.R] is the orifice resistance parameter and [[delta].sub.I] is the inertial end correction for sound radiating from the end of an unbaffled open tube. We used the results of Levine and Schwinger [20] for an infinitely thin wall tube

[[[delta].sub.I]/[r.sub.d]] = [[epsilon].sub.i0] + [[epsilon].sub.i2][(k[r.sub.d]).sup.2], [[[delta].sub.R]/[r.sub.d]][approximately equal to][1/4]k[r.sub.d] - [1/12][[19/12] - [[gamma].sub.e] - ln(k[r.sub.d])][(k[r.sub.d]).sup.3] (30)

where [[epsilon].sub.i0] = 0.6127, [[epsilon].sub.i2] = -0.1750, and [[gamma].sub.e] is Euler's constant. For convenience, we define the specific acoustic impedance [z.sub.rad] [equivalent to] ([[A.sub.d]/pc])[Z.sub.rad], and the admittances [y.sub.V] [equivalent to] ([pc/[A.sub.d]])([1/[Z.sub.V]]), and [y.sub.tube] = ([pc/[A.sub.d]])([1/[Z.sub.tube]]), and [y.sub.0] = ([pc/[A.sub.d]])([1/[Z.sub.0]]). With these definitions and substitution from Eq. (28), the admittance of the tube is

[y.sub.tube] = [y.sub.0][[1 + [z.sub.rad][y.sub.0]tanh([GAMMA][l.sub.d])]/[[z.sub.rad][y.sub.0] + tanh([GAMMA][l.sub.d])]]. (31)

A plot of [y.sub.v] is shown in Fig. 9.

We attempted to determine the source strength with the tube port plugged, however we were not able to obtain a consistent and repeatable seal around the plug and tubes. Instead, we started with the longest tube (1.6 m) mounted flush with the inner coupler wall, measured the acoustic pressure as a function of frequency, and then cut portions off the tube's free end to change the length without disconnecting the tube from the coupler. In this way, the baseline conditions at the coupler end were undisturbed and could be reliably eliminated.

[FIGURE 9 OMITTED]

Figure 10 shows the measured acoustic pressure with the 1.6 m long tube in place. The source strength [U.sub.0] was determined from the measured acoustic pressure combined with the calculated impedances of the coupler and tube from Eqs. (26)-(28). In terms of admittances, the source strength is

[FIGURE 10 OMITTED]

[U.sub.0] = [[A.sub.d]/[[rho]c]][p.sub.160]([y.sub.V] + [y.sub.160]) (32)

where [p.sub.160] is the measured acoustic pressure, [y.sub.160] is given by Eq. (31) for the 1.6 m tube. The theoretical tube impedance is plotted in Fig. 11, and the source strength deduced using Eq. (32) from the measured acoustic pressure with no adjustable parameters is shown in Fig 12.

[FIGURE 11 OMITTED]

[FIGURE 12 OMITTED]

The simple model for the source given in Appendix A predicts a linear frequency dependence for the source strength with a slope that is consistent with the slope of Re([U.sub.0]) in Fig. 12. At 1000 Hz, the measured source strength was 0.098 [mm.sup.3]/s compared to the predicted value 0.091 [mm.sup.3]/s with no adjustable parameters. The simple model in Appendix A does not predict the observed Im([U.sub.0]), however. Measurements of the acoustic pressure above 10 kHz revealed that the increase in Re(p) with frequency [and therefore the increase in Im([U.sub.0])] is due to the tail of a large resonance at 40 kHz, presumably of the membrane. For all the measurements presented here, the source strength was limited by the microphone's effective volume and membrane tension, but not limited by the impedance of the coupler or the attached tubes. We therefore used the same source strength function for all the tubes in order to deduce the tube impedances.

After shortening the duct by cutting off a section, leaving the attachment to the coupler unaltered, the acoustic pressure as function of frequency was again measured. The admittance of the tube with new length l was determined, with no adjustable parameters, from

[y.sub.l] = ([[[rho]c]/[A.sub.d]])[[U.sub.0]/[p.sub.l]] - [y.sub.V]. (33)

Figure 13 shows the measured acoustic pressure for the 1.4 m length, and the measured tube admittance is plotted in Fig. 14 as a function of frequency. Also plotted in Fig. 14 are the theoretical admittance (solid curve) and the deviations between the measured and calculated values. The root mean square difference between the measured and modeled specific admittances (both real and imaginary parts) over this frequency range was 0.018. The observed noise in the measured acoustic pressure mentioned previously accounts for the scatter in the deviation in Fig. 14. Figures 15 and 16 show similar plots of the acoustic pressure and the measured admittance for the 100 cm long tube.

[FIGURE 13 OMITTED]

[FIGURE 14 OMITTED]

[FIGURE 15 OMITTED]

[FIGURE 16 OMITTED]

We observed the largest systematic deviations between the measured and predicted admittances of the shortest tubes, where the admittance is more sensitive to errors in the length and to the details of the termination impedance. The attenuation length [l.sub.a] = [1/Re([GAMMA])]is a measure of how far the wave propagates down a long tube before damping out. Lower frequency waves travel further than higher frequency waves: [l.sub.a] = 1.4 m at 200 Hz, whereas [l.sub.a] = 0.22 m at 10 kHz. At 200 Hz, the acoustic pressure at the open end of the 20 cm long tube is attenuated by only 13 % of the acoustic pressure in the coupler. Once the wave leaves the open end, the attenuation length is significantly longer.

Our impedance measurements are comparable to the 1982 measurements by Rasmussen (10). He compared the measured and calculated acoustic transfer impedance of a coupler fitted with standard laboratory microphones and two narrow, open-ended tubes. The transfer impedance was measured using a reciprocity technique. Both tubes had a radius of 0.234 mm and a length of 1 m. Rasmussen reported a plot of the change (in dB) of the coupler impedance when the tubes were blocked compared to when the tubes were open. Rasmussen showed that a particular expression for the low-frequency acoustic impedance of a narrow tube (used to correct the coupler impedance for microphone calibrations) was subject to large systematic effects at sufficiently low frequency. Unfortunately, insufficient information was given to directly compare the measured and calculated impedance of a single tube without the coupler.

5. Discussion and Recommendations

Figure 17 shows [[DELTA]K/[kappa]] from Eq. (9) with [z.sub.0n] replaced by ka and [[bar.y].sub.d] due to the single-stage duct (dotted) and two-stage duct (solid) considered in Secs. 3.3 and 3.4 plotted as a continuous function of ka. The predicted perturbations of the radial modes of a spherical cavity (with [alpha] = 5 cm) are found for the values of ka indicated by the arrows. The perturbations of the (0,2) mode from the single-stage duct are (0.20 + 10.7i)x [10.sup.-6] and (0.02 + 10.9i)x [10.sup.-6] at 0.02 MPa and 0.42 MPa, respectively. The perturbations of the (0,2) mode from the two-stage duct are (0.6 + 2.5i)x [10.sup.-6] and (-0.08 + 1.1i)x [10.sup.-6] at 0.02 MPa and 0.42 MPa, respectively. At the higher pressure (0.4 MPa), the modes of the sphere coincide with the anti-resonances of the short duct since we chose the length of the short duct [l.sub.d] = a. The rapid oscillations that occur near and below ka = 1 are due to resonances in the 3 m long duct.

[FIGURE 17 OMITTED]

The perturbations for the longitudinal modes of a (5 cm radius) cylindrical cavity, from Eq. (10) with l[pi] replaced by kL, are obtained by multiplying the vertical axes in Fig. 17 by [(0.2m)/L]. However, the 2-stage arrangement with [r.sub.d] < [r.sub.d]', used to generate the plots, is not optimal for a cylindrical cavity. For the quarter-wave duct, discussed in Sec. 3.2, with [r.sub.d] = 0.7 mm, [r.sub.d]' = 0.35 mm, [l.sub.d] = 1.5L, and L = 2R, the perturbations of the two lowest even-symmetry modes (kR = [pi] and 2[pi]) at 0.02 MPa are (4.1 + 32.7i)x [10.sup.-6] and (0.03 + 16.2i)x [10.sup.-6]; at 0.4 MPa the perturbations are (5.4 + 14.1i)x [10.sup.-6] and (3.5 + 18.4i) x [10.sup.-6], respectively. With this arrangement, two ducts are necessary to flow the test gas through the resonator. We recommend using two cylindrical resonators, one twice as long as the other, to take advantage of the cancellation of the end-plate perturbations at the same frequency. For this reason, the ducts for flowing gas and for remote transducers, if needed, should be placed on the resonator's end plates.

To improve the experimental measurements of the admittance of small-diameter ducts, we recommend the following improvements in decreasing order of importance: 1) controlling the temperature and static pressure of the gas medium to reduce the random noise in the acoustic pressure, 2) devising a method to remove and reattach the tube such that the admittance is reproducible, so that the tube length can be determined more accurately and the coupler's impedance can be measured directly, 3) using argon instead of air as the gas medium to reduce the uncertainty in the gas properties, and 4) blocking the end of the tube opposite the coupler or using another coupler to better define the terminal impedance.

We have examined the perturbations of the modes of an acoustic thermometer caused by circular ducts used either for gas flow or as acoustic waveguides coupled to remote transducers. We calculated the acoustic admittance of circular ducts using a model based on transmission line theory. We used the admittance to calculate the perturbations to the resonance frequencies and half-widths of the modes of spherical and cylindrical acoustic resonators as functions of the duct's radius, length, and the locations of the transducers along the duct's length. We measured the specific acoustic admittances of a series of ducts between 200 Hz and 10 kHz in ambient air and compared the results with theory. For a 1.4 mm inside-diameter, 1.4 m long tube, the root mean square difference between the measured and modeled specific admittances over this frequency range was 0.018 (the magnitude of the specific admittance was nominally one).

6. Appendix A. Condenser Microphone as a Source

A schematic diagram of the Bruel & Kjaer 4135 condenser microphone is shown in Fig. A1. The properties of the 4135 are listed in Table A1. The membrane has a thickness [t.sub.x] and is stretched in tension over an annular insulator (quartz). The membrane flexes with an effective radius [a.sub.x]. The gap [h.sub.x] separates the membrane from a backplate with radius [b.sub.x]. The membrane and the backplate form the two electrodes of a parallel-plate capacitor with capacitance [C.sub.x] = [[[[epsilon].sub.0][pi][b.sub.x.sup.2]]/[h.sub.x]]. When used as a detector, the microphone is biased with a DC voltage of 200 V, and the charging current resulting from motion of the membrane is detected. However, when a condenser microphone is used as a source with sinusoidal drive and no DC bias, the sound waveform it generates is a sinusoid whose frequency is twice the excitation frequency. An advantage to this (2[Florin]) mode of operation is that cross talk between the high voltage excitation and the low voltage of nearby detectors is virtually eliminated.

[FIGURE A1 OMITTED]

Table A1. Properties of B & K 4135 microphone cartridge used a sound source Property Source Symbol Value Unit membrane measured [a.sub.x] 2.13 mm radius membrane measured [t.sub.x] 2.54 m thickness backplate measured [b.sub.x] 1.74 mm radius gap calculated [h.sub.x] 13.0 m membrane calculated [[sigma].sub.M] 0.0223 kg/[m.sup.2] mass per unit area capacitance manufacturer [C.sub.x] 6.4 pF membrane manufacturer [chi] 1.5 x m/Pa compliance [10.sup.-10] microphone manufacturer [V.sub.x] 0.6 [mm.sup.3] equivalent volume

A very detailed model of condenser microphones is given in Ref. (21), but is beyond the scope of this article. Our objective in this appendix is to describe the low-frequency behavior of a condenser microphone used as a source. We solve a simplified equation of motion for a membrane under tension whose displacement from equilibrium is y. Additional forces are included to account for the reaction of the gas in the microphone volume and the surrounding environment. Thermoacoustic dissipation is neglected.

If we define y as positive for upward displacement, then a simplified equation of motion is

[[sigma].sub.M][[[[partial derivative].sup.2]y]/[[partial derivative][t.sup.2]]] = T[[nabla].sup.2]y + [p.sub.E] - [DELTA]p. (A1)

The first term on the right hand side of Eq. (Al) is the restoring force per unit area due to the membrane tension, [p.sub.E] is the force per unit area from the applied electric field E

[p.sub.E] = - [1/2][[epsilon].sub.0][E.sup.2] = - [[epsilon].sub.0]/2[h.sub.x.sup.2][V.sup.2], (A2)

and [DELTA]p = [p.sub.a] - [p.sub.x], where [p.sub.a] and [p.sub.x] are the acoustic pressures generated in front of and behind the membrane, respectively. The applied voltage V(t) = [V.sub.s] [MATHEMATICAL EXPRESSION NOT REPRODUCIBLE IN ASCII] is at frequency [[Florin].sub.s], but the electric force on the membrane oscillates at 2[[Florin].sub.s] and has a DC component. Since we are only concerned with the AC response, we replace [V.sup.2] in Eq. (A2) by [V.sub.rms.sup.2] [e.sup.i[omega]t] with [omega] = 2[[omega].sub.s]. The steady-state response of the driven membrane displacement y(t) is also proportional to [e.sup.i[omega]t].

The source strength is defined as the rate of volume displacement averaged over the membrane area

[U.sub.0] = [pi][a.sup.x.sup.2]<y> = i[omega][pi][a.sub.x.sup.2]<y>. (A3)

If the acoustic impedance of the medium in front the transducer is [Z.sub.L] and the impedance of the medium in the space inside the transducer is [Z.sub.x], then we have

[p.sub.a] = [Z.sub.L][U.sub.0] (A4)

and

[p.sub.x] = - [Z.sub.x][U.sub.0]. (A5)

We rewrite Eq. (A1) as

[[nabla].sup.2]y + [K.sup.2]y = [[[[epsilon].sub.0][V.sub.rms.sup.2][e.sup.i[omega]t]]/[2[h.sub.x.sup.2]T]] + [[i[omega][pi][a.sub.x.sup.2]]/T]([Z.sub.L] + [Z.sub.x])<y> (A6)

where [K.sup.2] = [[sigma].sub.M] [[[omega].sup.2]/T]. The steady-state solution for Eq. (A6) can be expanded in terms of the normal modes of a circular membrane with a fixed edge, namely [J.sub.m] ([[[xi].sub.mn]r/[a.sub.x]]) cos (m[theta]), where [J.sub.m] ([[xi].sub.mn]) = 0. Due to the axial symmetry of the drive force, however, only the axially symmetric modes (m = 0) will be considered in the model, i.e.,

y = [[infinity].summation over (n = l)][A.sub.0n]][J.sub.0]([[[[xi].sub.0n]r]/[a.sub.x]])[e.sup.i[omega]t]. (A7)

The coefficients [A.sub.0n] are obtained by substituting (A7) into (A6) and integrating over the membrane area.

For simplicity, we assume the membrane and backplate have the same diameters.

[A.sub.0n] = - [[2[a.sub.x.sup.2]( - [p.sub.E] + [DELTA]p)]/[T([[xi].sub.[0n].sup.2] - [K.sup.2][a.sub.x.sup.2])[[xi].sub.0n][J.sub.1]([[xi].sub.0n])]] (A8)

Equation (A8) predicts the lowest mode of the membrane occurs when [Ka.sub.x] = [[xi].sub.01] [approximately equal to] 2.4048 or about 74 kHz. The average membrane displacement in the low-frequency limit [Ka.sub.x] [much less than] [[xi].sub.01] is

<y> = [[ - [[epsilon].sub.0][V.sub.[rms].sup.2][chi]/(2[h.sub.x.sup.2])]/[1 + i[omega][pi][a.sub.x.sup.2]([Z.sub.c] + [Z.sub.x])[chi]]] (A9)

where we have used the property [[infinity].summation over (n=1)]([1/[[xi].sub.0n.sup.2]]) = 1/32] and identified the membrane compliance [chi] = [[a.sub.x.sup.2]/(8T)]. We can estimate [Z.sub.L] and [Z.sub.x] assuming they represent simple volumes, [V.sub.L] and [V.sub.x], respectively, with the expressions [Z.sub.L] = [p[c.sup.2]/(i[omega][V.sub.L])] and [Z.sub.x] = [p[c.sup.2]/(i[omega][V.sub.x])]. For our application, the volume of the coupler (134 [mm.sup.3]) is very large compared to the transducer's equivalent volume (0.6 [mm.sup.3]), so we can neglect the impedance [Z.sub.L]. This is important because it means that the source strength will not depend strongly on the coupler or the attached tubes.

Finally, the source strength from Eq. (A3) in the low-frequency limit is (neglecting [Z.sub.L])

[U.sub.0] = [[ - i[omega][pi][a.sub.x.sup.2][V.sub.[rms].sup.2][[epsilon].sub.0][chi]/(2[h.sub.x.sup.2])]/[1 + [chi][pi][a.sub.x.sup.2][rho][c.sup.2]/[V.sub.x]]] (A10)

In ambient air ([rho][c.sup.2] = 1.41 x [10.sup.5] Pa) at 1 kHz, Eq. (A10) gives

|[U.sub.0]|[approximately equal to](0.091[mm.sup.3]/s), (A11)

using values from Table Al.

7. References

(1) Michael R. Moldover, Acoustic and microwave resonances applied to measuring the gas constant and the thermodynamic temperature, IEEE Transactions on Instrumentation and Measurement 38, 217 (1989).

(2) M. R. Moldover, S. J. Boyes, C. W. Meyer, and A. R. H. Goodwin, Thermodynamic temperatures of the triple points of mercury and gallium and in the interval 217 K to 303 K, J. Res. Natl. Inst. Stand. Technol. 104, 11 (1999); M. R. Moldover, S, J. Boyes, C. W. Meyer, and A. R. H. Goodwin, Primary Acoustic Thermometry from 217 K to 303 K, TEMPMEKO, Delft, The Netherlands, (1999).

(3) D. C. Ripple, D. R. Defibaugh, M. R. Moldover, and G F. Strouse, Techniques for primary acoustic thermometry to 800 K, in Temperature: Its Measurement and Control in Science and Technology. Proceedings of the 8th International Temperature Symposium 21-24 October 2002, Chicago, 11., vol. 7, ed. By D. C. Ripple (AIP Conf Proc, Melville, New York, 2003), pp. 25-30.

(4) G. F. Strouse, D. R. Defibaugh, M. R. Moldover, and D. C. Ripple, Progress in primary acoustic thermometry at NIST: 273 K to 505 K, in Temperature: Its Measurement and Control in Science and Technology. Proceedings of the 8th International Temperature Symposium 21-24 October 2002, Chicago, II., vol. 7, ed. By D. C. Ripple (AIP Conf Proc., Melville, New York, 2003), pp. 31-36.

(5) D. C. Ripple, G. F. Strouse, and M. R. Moldover, Acoustic thermometry results from 271 K to 552 K, Int. J. Thermophys. 28, 1789-1799(2007).

(6) J. B. Mehl, M. R. Moldover, and L. Pitre, Designing quasi-spherical resonators for acoustic thermometry, Metrologia 41, 295-304 (2004).

(7) G. Benedetto, R. M. Gavioso, R. Spagnolo, P. Marcarino, and A. Merlone, Acoustic measurements of the thermodynamic temperature between the triple point of mercury and 380 K, Metrologia 41, 74-98 (2004).

(8) K. A. Gillis, M. R. Moldover, and A. R. H. Goodwin, Accurate measurements in gases under difficult conditions, Rev. Sci. Instrum. 62, 2213-2217 (1991).

(9) D. R. Ripple, private communication.

(10) K. Rasmussen, Note on the Acoustic Impedance of Narrow Tubes, Acoustica 51, 72-73 (1982).

(11) D. Rodrigues, C. Guianvarc'h, J.-N. Durocher, M. Bruneau, A.-M. Bruneau, A method to measure and interpret input impedance of small acoustic components, J. Sound and Vib. 315,890-910(2008),

(12) K. A. Gillis, J. B. Mehl, and M. R. Moldover, Theory of the Greenspan Viscometer, J. Acoust. Soc. Am. 114, 166 (2003).

(13) I. B. Crandall, Theory of vibrating systems and sound, (Van Nostrand, New York, 1927), pp 229-241.

(14) T. J. Quinn, A. R. Colclough, and T. R. D. Chandler, A new determination of the gas constant by an acoustical method, Philosophical Transactions of the Royal Society of London. Series A: Mathematical and Physical Sciences 283, 367-420 (1976).

(15) P. M. Morse and K. U. Ingard, Theoretical Acoustics (McGraw-Hill, New York, 1968), Sec. 9.4.

(16) K. A. Gillis and M. R. Moldover, Designing ducts for acoustic thermometers, to be published.

(17) NIST Reference Fluid Thermodynamic and Transport Properties Database (REFPROP): Version 8.0.

(18) R. F. Berg, Simple flow meter and viscometer of high accuracy for gases, Metrologia 42, 11-23 (2005).

(19) F. B. Daniels, Acoustic impedance of enclosures, J. Acoust. Soc.Am. 19,569-571 (1947).

(20) H. Levine and J. Schwinger, On the radiation of sound from an unflanged circular pipe, Phys Rev 73, 383 (1948); H. Levine, On the theory of sound reflection in an open-ended cylindrical tube, J. Acoust. Soc. Am. 26, 200-211 (1954).

(21) A. J. Zuckerwar, Principles of Operation of Condenser Microphones, in AIP Handbook of Condenser Microphones, ed. G. S. K. Wong and T. E. W. Embleton (AIP Press, New York, 1995).

(1) current address: Heat Division, National Institute of Metrology (NIM), Beijing 100013, China.

(2) Certain commercial equipment, instruments, or materials are identified in this paper to foster understanding. Such identification does not imply recommendation or endorsement by the National Institute of Standards and Technology, nor does it imply that the materials or equipment identified are necessarily the best available for the purpose.

About the authors: Dr. Keith A. Gillis is a physicist and acoustician in the Fluid Metrology Group in the Process Measurements Division of the NIST Chemical Science and Technology Laboratory. Dr. Hong Lin is in the Heat Division at the National Institute of Metrology (NIM), Beijing, China and was a Guest Researcher at NIST. Dr. Michael R. Moldover is a NIST Fellow and Leader of the Fluid Metrology Group in the Process Measurements Division of the NIST Chemical Science and Technology Laboratory. The National Institute of Standards and Technology is an agency of the U.S. Department of Commerce.

K. A. Gillis, H. Lin, (1) and M. R. Moldover

National Institute of Standards and Technology, Gaithersburg, MD 20899-0001

keith.gillis@nist.gov

linhong@nim.ac.cn

michael.moldover@nist.gov

Accepted: May 19, 2009

Available online: http://www.nist.gov/jres

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Author: | Gillis, K.A.; Lin, H.; Moldover, M.R. |
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Publication: | Journal of Research of the National Institute of Standards and Technology |

Article Type: | Report |

Geographic Code: | 1USA |

Date: | Sep 1, 2009 |

Words: | 10854 |

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