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REVIEW 3 major objections 5 minor 50 references

Intrinsic aeroacoustic instabilities in the crosstalk apertures of can-annular combustors

T0 review · 3 major / 5 minor · reviewed 2026-08-12 · deepseek-v4-flash

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Pith's one-line read Crosstalk gaps between combustor cans can whistle on their own, with no acoustic feedback from the duct ends.

desk verdict A careful first experimental map of crosstalk-aperture whistling, but the 'intrinsic instability' label outruns the evidence because the choked-vane reflection path is never closed. read the letter →

arxiv 2411.18283 v1 pith:XGXXBYQS submitted 2024-11-27 physics.flu-dyn

Audrey Blondé , Khushboo Pandey , Bruno Schuermans , Nicolas Noiray This is my paper · ORCID
classification physics.flu-dyn
keywords can-annularcombustorscrosstalkapertureaeroacousticinstabilitiesintrinsicinstabilityStrouhalscalingshear-layerself-oscillationchokedturbinevaneslargeeddysimulation
verification ladder T0 review T1 audit T2 compute T3 formal

The pith

A machine-rendered reading of the paper's core claim, the machinery that carries it, and where it could break.

The reading

This paper reports that the narrow crosstalk opening between two neighbouring combustor channels can whistle loudly on its own, with no flame and no acoustic feedback from the duct ends. Using a laboratory rig whose upstream and downstream terminations are anechoic above 600 Hz, the authors observe self-sustained oscillations whose frequency falls with aperture length and collapses onto a constant Strouhal number. They interpret this as an intrinsic aeroacoustic instability: the shear layer spanning the aperture oscillates and radiates plane waves upstream, without a longitudinal acoustic mode locking the frequency. Compressible large-eddy simulations reproduce the whistling and locate the sound source in the fluctuating Lamb vector inside the aperture. The result matters for can-annular gas turbines because such gaps sit between every pair of cans, and self-oscillation there can be as damaging as thermoacoustic vibration.

What carries the argument

The load-bearing object is the crosstalk aperture itself: a small gap between two square channels, bounded upstream by the splitting-plate trailing edge and downstream by choked turbine vanes, with low-Mach grazing flow on both sides. Its behaviour is governed by a Strouhal number based on the aperture length, $St = f(d + r_v/2)/U$, where $d$ is the gap distance, $r_v$ the vane leading-edge radius, and $U$ the channel velocity; the collapse of all whistling peaks onto one constant Strouhal number is the evidence that a convective shear-layer instability sets the frequency. The other essential elements are the anechoic terminations, verified by multi-microphone measurement of reflection coefficients, which exclude longitudinal acoustic feedback, and the fluctuating Lamb vector $\omega \times u$, whose projection on the acoustic velocity identifies the region of sound production in the aperture.

What would settle it

A decisive check would be to measure the upstream reflection coefficient at the exact whistling frequency for each geometry; if it is not small at those frequencies, then the claim that longitudinal modes play no role is unsupported. Alternatively, replacing the anechoic terminations with highly reflective walls and observing a frequency shift to a duct resonance would show that boundary feedback participates after all.

Watch

Extended reading notes

Core claim

On the paper's own terms, the central discovery is that intense whistling at the crosstalk aperture is an intrinsic aeroacoustic instability, not an acoustically coupled duct mode. Because the inlet and outlet terminations absorb sound above 600 Hz, the observed peaks at 2–5 kHz cannot be maintained by reflection from the rig boundaries; instead, the hydrodynamic shear layer across the aperture self-oscillates and radiates plane acoustic waves upstream in both channels. The oscillation frequency obeys $St = f(d + r_v/2)/U$ with $St \approx 0.62$ for rectangular and $0.51$ for round upstream edges in the misaligned vane configuration, and the probability density of the band-passed pressure changes from Gaussian to bimodal as the aperture grows, signalling a transition to a self-oscillating limit cycle. The same instability is reproduced in compressible large-eddy simulations, where the source region is identified through the fluctuating Lamb vector.

Load-bearing premise

The load-bearing premise is that the terminations are truly anechoic at all whistling frequencies and that the choked vane passage itself provides no hidden acoustic reflection path back to the aperture.

Editorial extensions

If this is right

  • Whistling frequency at a given geometry can be predicted from the Strouhal number once the channel velocity is known.
  • The onset of whistling can be suppressed or delayed by changing the shape of the aperture's upstream edge, rectangular versus round, and by aligning the splitting plate with a vane.
  • In a real can-annular combustor, acoustic reflections from burners and flames would add to the intrinsic source, potentially producing a stronger aero-thermo-acoustic limit cycle than the pure aeroacoustic one.
  • The Gaussian-to-bimodal probability-density transition gives a robust experimental marker for detecting the instability threshold.
  • Because the whistling is intrinsic, it can occur in non-reactive flow and may be misattributed to flame-acoustic coupling in engines.

Reading between the lines

Editorial extensions of the paper, not claims the author makes directly.

  • If the instability is truly intrinsic, then any two neighbouring cans whose outlet gap meets the same Strouhal and geometry conditions should whistle even with perfectly non-reflecting boundaries, so engine tests with reflective boundaries may under- or over-estimate the amplitude depending on phase.
  • A testable extension is to vary the vane leading-edge radius $r_v$ and check that the whistling frequency shifts through the same Strouhal relation, which would confirm that the relevant length scale is $d + r_v/2$ rather than $d$ alone.
  • The same mechanism might apply to other two-sided grazing-flow apertures with a downstream choked passage, such as bleed-air systems or inter-stage gaps, wherever a thin shear layer spans a narrow opening.
  • The simulations suggest that turbulent perturbations visibly modulate the amplitude of the self-oscillation, so a stochastic model of the unstable shear-layer mode could predict the observed pressure statistics without resolving the full turbulence.
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Editorial analysis

A structured set of objections, weighed in public.

Desk editor's note, referee report, and a circularity audit.

Referee Report

3 major / 5 minor

Summary. This paper reports an experimental and numerical study of self-sustained whistling at the crosstalk aperture between two choked-flow channels that model the combustor-to-turbine interface of a can-annular gas turbine. The rig has nominally anechoic upstream and downstream terminations, and the aperture geometry is varied in terms of axial length, edge shape, and vane alignment. The authors observe intense narrow-band acoustic peaks for several configurations, with a peak frequency that decreases as the aperture length increases, and they interpret the phenomenon as an intrinsic aeroacoustic instability governed by Strouhal scaling of the shear layer in the aperture. Compressible LES reproduces the whistling for two of the three simulated cases, and the paper uses the simulations to localize the sound source via the fluctuating Lamb vector. The claimed practical relevance is that such crosstalk whistling could be misattributed to thermoacoustic flame feedback in real engines.

Significance. If the intrinsic-instability interpretation is correct, the result is significant: it would demonstrate that a purely hydrodynamic shear-layer feedback at the aperture can produce high-amplitude self-sustained oscillations without a global acoustic mode, and it would establish a new mechanism relevant to can-annular combustor design. The experimental dataset is valuable: it systematically varies aperture length, edge geometry, and vane alignment, and it uses PDF shape as a stability indicator. The LES reproduces the main trends and provides a plausible source region, and the paper is honest about the one discrepant LES case. The main weakness is that the evidence does not fully exclude a local acoustic feedback path involving the choked vane throat, so the central claim needs additional support before the paper can be accepted as written.

major comments (3)
  1. [Section 3.1 / Section 2.3] The conclusion that the whistling is an intrinsic aeroacoustic instability is not fully secured. The anechoic character of the upstream and downstream horns, characterized above 600 Hz, excludes longitudinal modes spanning the entire rig, but it does not exclude a short local feedback loop: shear-layer oscillation at the aperture radiates downstream, reflects from the choked vane throat a few millimeters away, and returns to seed the shear layer. The microphones x5-x8 characterize the downstream horn from the downstream side of the vanes; they do not measure the upstream-looking reflection coefficient of the choked vane passage. The introduction itself cites [38] to state that choked nozzles reflect sound. To support the central claim, the authors should either measure or model the reflection presented to upstream-traveling waves by the vane passage, or provide a direct test such as an LES with the vane throat artificially made anechoic, showing that the oscillation persists without that reflection.
  2. [Section 3.1, Eq. (2) and Fig. 3c] The Strouhal numbers 0.62, 0.51, 0.55, and 0.41 are extracted from the measured peak frequencies at a single flow velocity and then used to draw the dashed scaling lines; calling this 'Strouhal scaling enables prediction' overstates the evidence, because the constants are calibrated to the same data. The data do clearly show that the whistling frequency decreases with aperture length, and a constant-St collapse is a reasonable summary, but it should be presented as a fit rather than a predictive test. Please report the fitted constants with uncertainties and, if predictive power is claimed, validate against an independent condition such as a different flow velocity or a different vane radius.
  3. [Section 4.2, d = 7.2 mm] The LES predicts self-sustained oscillations for d = 7.2 mm, while the experiment shows a stable Gaussian PDF for the same geometry; the paper attributes this to proximity of the instability threshold without quantitative support. This case is also one of the two used in Section 4.3 for the Lamb-vector source analysis. The discrepancy weakens the claim that the LES 'remarkably reproduce the whistling phenomenon.' Please provide a quantitative argument for the threshold-sensitivity interpretation, for example a linear growth-rate estimate, a sensitivity study to small geometric perturbations, or a stability map, so that the mismatch is not left as an ad hoc explanation.
minor comments (5)
  1. [Section 3.1, first paragraph] The sentence 'In Fig. 2a, one can see a sharp peak for all crosstalk opening' appears to refer to Fig. 3a, the acoustic spectra, not Fig. 2a, the rig overview.
  2. [Section 4.3, Fig. 8 discussion] The text states 'an alternance of upward (red) and downward (red) flow deflection'; the two colors should be different, likely 'downward (blue)', or the figure color scheme should be described accurately.
  3. [Eq. (1)] The isentropic choked-mass-flow equation is typeset with an ambiguous exponent; please use standard display math so that the exponent (γ+1)/(2(γ-1)) is clear.
  4. [Appendix] The sentence 'an increase in the mass flow rate is accompanied with an of the mean pressure' is incomplete; it should read 'accompanied by an increase of the mean pressure.'
  5. [Section 2.3] The statement that 'most of the acoustic energy travelling towards the terminations is absorbed' is qualitative; please report the numerical range of |R| above 600 Hz so the anechoic criterion is quantitative and reproducible.

Circularity Check

1 steps flagged · score 4.0 of 10

Strouhal 'prediction' is a calibration dressed as a prediction; the intrinsic-instability claim itself is not circular but rests on an unmeasured vane-throat reflection assumption.

  1. fitted input called prediction [Section 3.1, Eq. (2), Fig. 3c; Section 5 (Conclusion)]
    "The dashed black lines in Fig. 3c represent the Strouhal scaling. The frequencies for the rectangular and round edges scale with a Strouhal number of 0.62 and 0.51, respectively. [...] The Strouhal scaling enables prediction of the of the peak frequency of the self-oscillations."

    The Strouhal constants 0.62, 0.51, 0.55 and 0.41 are obtained by drawing scaling lines through the measured dominant peak frequencies in Figs. 3c and 5c, with the length scale d+rv/2 chosen a posteriori to collapse those same data. Therefore claiming that the scaling 'enables prediction of the peak frequency' is a restatement of the fit rather than an independent predictive test. This circularity is partial: the main intrinsic-instability claim does not depend on the exact St values, and is separately supported by the d-dependence of the peaks and by LES with anechoic NSCBC conditions.

full rationale

One genuine circular step exists: the Strouhal numbers are fitted to the measured whistling frequencies and then the same scaling is called a prediction. This is a fitted-input-called-prediction. However, the central claim — that the whistling is an intrinsic aeroacoustic instability — is not forced by that fit. The decrease of frequency with aperture length, the LES reproducing self-oscillation with nearly anechoic inlet/outlet NSCBC, and the bimodal PDF transition are independent observations. The paper's self-citations ([27], [38], [11]) are contextual and not load-bearing; no uniqueness theorem is imported. A separate correctness caveat, not a circularity, is that the anechoic-character claim is validated only for the far inlet/outlet horns above 600 Hz; the choked vane passage itself is acknowledged in the introduction to reflect sound ([38]), and its upstream-facing reflection coefficient is not measured, so a short local feedback loop involving the vane throat is not excluded. Score is 4 instead of 6 because the main result retains independent content.

Assumptions & free parameters 5 free parameters · 5 assumptions · 0 invented entities

No new physical entities are introduced; the whistling is interpreted as a known shear-layer feedback mechanism. The main fitted inputs are the four Strouhal constants and the effective length offset, all calibrated to the same experimental data that the scaling is claimed to predict.

free parameters (5)
  • Strouhal number, rectangular edge, misaligned vanes = 0.62
    Obtained by fitting Eq. (2) to the measured peak frequencies in Fig. 3c; the same data are then said to obey Strouhal scaling.
  • Strouhal number, round edge, misaligned vanes = 0.51
    Fitted to round-edge peak frequencies in Fig. 3c.
  • Strouhal number, rectangular edge, aligned vanes = 0.55
    Fitted to aligned-vane peak frequencies in Fig. 5c, for cases with peaks above 90 dB.
  • Strouhal number, round edge, aligned vanes = 0.41
    Fitted to aligned-vane round-edge peak frequencies in Fig. 5c.
  • Effective aperture length offset rv/2 = 3.8 mm (rv = 7.6 mm)
    The term d + rv/2 in Eq. (2) is a chosen length scale that collapses the frequency data; the offset is not derived from theory.
assumptions (5)
  • standard math Choked-flow isentropic relations, Eq. (1), determine the critical area and guarantee sonic conditions at the vanes.
    Used in Section 2.2 to set operating conditions.
  • domain assumption The measured upstream and downstream reflection coefficients are small above 600 Hz, so the terminations are anechoic in the whistling range.
    Section 2.3 and Fig. 2a; underpins the intrinsic-instability interpretation.
  • domain assumption Howe's energy corollary, with the Lamb vector as sound source, applies to this low-Mach, high-Reynolds aperture flow.
    Invoked in Section 4.3 to relate Lamb vector fluctuations to acoustic energy production.
  • domain assumption A bimodal PDF of band-pass filtered acoustic pressure marks a self-oscillating shear-layer mode, per Van der Pol oscillator statistics.
    Used in Sections 3.1 and 3.2 to infer stability thresholds from PDF shape.
  • domain assumption Smagorinsky SGS model with constant 0.17 and law-of-the-wall boundary layers adequately represent the turbulent channel flow in the LES.
    Section 4.1; affects quantitative fidelity of the whistling reproduction.

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Cite this review

Pith. "Pith review of Intrinsic aeroacoustic instabilities in the crosstalk apertures of can-annular combustors." pith.science (2026). https://pith.science/paper/XGXXBYQS

@misc{pith2026241118283,
  author       = {Pith},
  title        = {Pith review of: Intrinsic aeroacoustic instabilities in the crosstalk apertures of can-annular combustors},
  year         = {2026},
  howpublished = {\url{https://pith.science/paper/XGXXBYQS}},
  note         = {Machine review of arXiv:2411.18283}
}
read the original abstract

This paper presents an experimental and numerical study of aeroacoustic instabilities at the interface between neighbouring combustion chambers in modern heavy-duty gas turbines. A simplified laboratory-scale geometry of the gap separating the outlet of these chambers, just upstream of the turbine inlet in can-annular combustor architectures, is considered. It consists of two channels with anechoic and chocked conditions on the upstream and downstream sides respectively. Right before the choked-flow vanes which represent the turbine inlet, a small aperture leads to an aeroacoustic crosstalk between the channels. The dimensions and flow conditions are defined such that relevant Mach, Strouhal and Helmholtz numbers of gas turbines are reproduced. The alignment of the vanes with respect to the crosstalk aperture is varied. An intense whistling is observed for some conditions. The oscillation frequency depends on the aperture area and scales with the Strouhal number based on the aperture length. The upstream anechoic condition in each channel implies that no longitudinal acoustic mode participate to the mechanism of this whistling, which is in agreement with the Strouhal scaling of this intrinsic aeroacoustic instability. Compressible Large Eddy Simulations of the configuration have been performed and remarkably reproduce the whistling phenomenon. This work contributes to the understanding of aeroacoustic instabilities at the crosstalk apertures of can-annular combustors. It will help designing combustor-turbine interfaces to suppress them, which is important since the vibrations they induce may be as damaging as the ones from thermoacoustic instabilities.

Figures

Figures reproduced from arXiv: 2411.18283 by the authors.

Figure 1
Figure 1. (a-b) Illustration of a typical can-annular combustor (a [PITH_FULL_IMAGE:figures/full_fig_p004_1.png] view at source ↗
Figure 2
Figure 2. a) Overview of the test rig, continuously supplied by an air c [PITH_FULL_IMAGE:figures/full_fig_p009_2.png] view at source ↗
Figure 3
Figure 3. Acoustic data recorded for the misaligned vanes configur [PITH_FULL_IMAGE:figures/full_fig_p014_3.png] view at source ↗
Figures from the paper (7 more)
Figure 4
Figure 4. Figure 4: Reconstructed acoustic pressure fields for [PITH_FULL_IMAGE:figures/full_fig_p018_4.png]
Figure 5
Figure 5. Figure 5: Acoustic data recorded for the aligned vane configuratio [PITH_FULL_IMAGE:figures/full_fig_p020_5.png]
Figure 6
Figure 6. Figure 6: Large Eddy Simulations setup of the flow at the crosstalk a [PITH_FULL_IMAGE:figures/full_fig_p023_6.png]
Figure 7
Figure 7. Figure 7: Instantaneous pressure fluctuations obtained by subt [PITH_FULL_IMAGE:figures/full_fig_p024_7.png]
Figure 8
Figure 8. Figure 8: Phase-averaged transverse component of the flow velo [PITH_FULL_IMAGE:figures/full_fig_p027_8.png]
Figure 9
Figure 9. Figure 9: Time traces of the pressure fluctuations [PITH_FULL_IMAGE:figures/full_fig_p029_9.png]
Figure 10
Figure 10. Figure 10: a) Acoustic PSD for five different mass flow rates ˙m [PITH_FULL_IMAGE:figures/full_fig_p033_10.png]

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Reviewed August 12, 2026 · model on record in the stance chip above.