Stall-Warning Approach Based on Aeroacoustic Principle

Li, Fanyu; Li, Jun; Dong, Xu; Zhou, Youtian; Sun, Dakun; Sun, Xiaofeng

doi:10.2514/1.b35814

Cited by 17 publications

(6 citation statements)

References 38 publications

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“…Figure 9 represents the characteristic lines with different distortion and injection cases. The abscissa of flow coefficient and the ordinate of pressure rise coefficient are defined in equations (8)(9). Case A represents the uniform inflow condition; Case C, E and G represent the steady distortion condition; and Case B, D, F and H represent the steady injection under uniform inflow, steady distortion with 0.90%, 4.12% and 24.75% distortion intensity.…”

Section: Figure 8 Characteristic Signal At 1508% Cax Under Transientmentioning

confidence: 99%

“…The timely detection of spike and modal wave exists slight difference due to the different features of frequency, scale and propagation speed, etc. Currently, the prediction concerning spike is expanded from stall inception to pre-stall inception detection via considerable surveillance parameters monitoring the collapse of the blade pressure periodicity, such as auto- [4][5] and cross-correlation [6][7] coefficient, irregularity [8] and parameter Rc [9]. As for the modal wave stall inception, it was initial discovered by McDougall et al [3] via first harmonic of spatial Fourier analysis in the experiments.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic instability prediction using fast wavelet subjected to transient circumferential distortion in an axial flow compressor

Liu¹,

Li²,

Li³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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Fast wavelet tool was employed as an aerodynamic instability prediction tool in an isolated-rotor axial compressor with transient circumferential distortion. The spatial and time-resolved high-frequency pressure transducers were installed circumferentially and along blade chord direction to measure the dynamic pressure signal. In current work, the transient circumferential distortion was generated by a flat-baffle designed as adjustable distortion intensity of 0.90%, 4.12% and 24.75% with 25%, 50% and 75% span height to model the distortion generation process in actual compressors. Steady measurement results demonstrated that the stall margin deteriorated by 3.44%, 11.14% and 58.32% with steady circumferential distortion with 25%, 50% and 75% span distortion height, respectively. At the moment when transient circumferential distortion was generated, the characteristic line was suddenly transferred to steady distortion characteristic line and stall margin correspondingly deteriorated; and it returned to the characteristic line under uniform inflow condition with wider stall margin when distortion disappeared. Unsteady pressure was measured and analysed using fast wavelet to predict the aerodynamic stability of axial compressor with transient circumferential distortion. Fast wavelet results showed that after the transient circumferential distortion generated, the amplitude of high frequency reconstructed signal (characteristic signal) correspondingly increased, which means the compressor turned into less stable status. When stability enhancement strategy, steady tip air injection, was implemented, the stability was enhanced by 5.21%, 4.44%, 3.39% and 8.88% using 0.41% design mass flow injection under uniform inflow, steady circumferential distortion with 25%, 50%, and 75% span distortion height, respectively. The amplitude of characteristic signal decreased with injected tip air in all cases. Accordingly, the capability of fast wavelet to predict the stability is verified with circumferential distortion. Therefore, the fast wavelet is a promising aerodynamic stability prediction tool in axial compressor.

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Section: Figure 8 Characteristic Signal At 1508% Cax Under Transientmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aerodynamic instability prediction using fast wavelet subjected to transient circumferential distortion in an axial flow compressor

Liu¹,

Li²,

Li³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

View full text Add to dashboard Cite

show abstract

“…At the design point, the current signal is almost accordant with the signal one shaft period before. At the near stall point, because the flow separation and vortex shedding occur more frequently, which affect the circulation of blades, the pressure signals of two contiguous revolutions are quite different from each other [15].…”

Section: Stall Warning Approachmentioning

confidence: 99%

“…If the calculating window is extended from 3 blades to 47 blades (one revolution), the range of Rc for and is almost identical (Fig.11). According to reference [15], in a compressor working at near stall point, the perturbance mainly consists of flow separation and vortex shedding on the blade. The scale of these flow phenomenon usually covers two to three blades, so a calculating window covering three blades is an appropriate choice.…”

Section: Signal Simulationmentioning

confidence: 99%

“…All these researches above utilized the deterioration of blade-passing periodicity near stall but did not have enough theoretical analysing for the mechanism behind this phenomenon. Li et al [15] considered the collapse of periodicity could reflect the evolution of stall precursor. From this perspective, they explained the mechanism of this phenomenon by using aero-acoustic theory and vortex theory.…”

Section: Introductionmentioning

confidence: 99%

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Application of Stall Warning Approach with Stall Precursor Suppressed Casing Treatment on a Two-Stage Compressor

Xu¹,

Xu²,

Li³

et al. 2019

Proceedings of Global Power &Amp; Propulsion Society

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A stall-warning approach based on aero-acoustic theory is studied in this paper. For this stall warning approach, a parameter Rc is defined to measure the periodicity of the blade-passing signal. Signal simulation is used to investigate the mechanism of the stall warning approach. The results suggest that the value of Rc is influenced by the power of the perturbance. The experiments on a 2-stage compressor indicate this stall warning approach can generate a warning signal several seconds before the stall. It is demonstrated in this paper that the stall warning approach can detect the distribution and evolution of stall precursors. According to the distribution of the stall precursors, the partial SPS casing treatment is applied and realized a stabilization of compressor.

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Experimental and Numerical Studies on Compressor Nonlinear Behaviors with Inlet Distortion and Their Interaction

Li¹,

Zhou²,

Song³

2022

Nonlinear Systems and Complexity

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Stall-Warning Approach Based on Aeroacoustic Principle

Cited by 17 publications

References 38 publications

Aerodynamic instability prediction using fast wavelet subjected to transient circumferential distortion in an axial flow compressor

Aerodynamic instability prediction using fast wavelet subjected to transient circumferential distortion in an axial flow compressor

Application of Stall Warning Approach with Stall Precursor Suppressed Casing Treatment on a Two-Stage Compressor

Experimental and Numerical Studies on Compressor Nonlinear Behaviors with Inlet Distortion and Their Interaction

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