Experimental investigation of aeroelastic instabilities in an aeroengine fan: Using acoustic measurements

Li, Zepeng; Wang, Yanan; Qiao, Baijie; Wen, Bin; Chen, Xuefeng

doi:10.1016/j.ast.2022.107927

Cited by 8 publications

(2 citation statements)

References 29 publications

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“…For the higher sound pressure level which exceeds the measuring range of reverberation chamber test, acoustic wave tube test is more suitable. This method has been used widely in the measurement of noise of fan, engine, and other noises in the aerospace field [44][45][46][47][48][49][50][51][52][53]. For higher sound pressure level measurement, more and more research work could be found in the previous papers.…”

Section: Acoustic Test Methodsmentioning

confidence: 99%

A Review on the High Sound Pressure Level Acoustic Measurement in the Aerospace Field

Chen

Qin

et al. 2023

Journal of Sensors

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Noise could occur anywhere in the aerospace and other fields and has a great influence on the operation of the aircraft. The control of the sound emission has attracted a lot of attention from the economic and environmental aspects. Firstly, the noise is annoying for the passengers and pilot and may increase the risk to be exposed for the military applications. Secondly, the sound emission may pose a great damage and threat to the engine equipment due to the strong pressure oscillation. In addition, the combustion noise may also have a great influence on the combustion process in the engine, which may lead to the emission increase and low-efficiency operation. The noise emission measurement is necessary and very important for the research in aerospace field. The aircraft in aerospace field usually works in the extreme environment, and the noise emission is within a high sound pressure level, which is quite from the acoustic measurement in other fields. Thus, we give a short review to introduce the high sound pressure level acoustic measurement in the aerospace field.

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Section: Acoustic Test Methodsmentioning

confidence: 99%

A Review on the High Sound Pressure Level Acoustic Measurement in the Aerospace Field

Chen

Qin

et al. 2023

Journal of Sensors

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“…The compressor design has an increasing trend towards higher blade loading and thinner blade shape. However, this also increases the occurrence probability of aeroelastic instability which can be mainly divided into forced response, nonsynchronous vibration, acoustic resonance and flutter [1,2]. The former three types rely on the unsteady aerodynamic forces generated by external disturbances.…”

Section: Introductionmentioning

confidence: 99%

Influence mechanism of tip clearance on flutter stability with different aerodynamic coupling effects for transonic compressor

Xin,

He,

et al. 2024

J. Phys.: Conf. Ser.

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Flutter is a highly destructive aeroelastic problem in modern compressors, which hinders the improvements of aero-engine performance and reliability. Because the aerodynamic work is mainly concentrated in the blade tip region, the tip clearance which is associated to the complex tip clearance flow has a considerable effect on the flutter stability. In this paper, in order to investigate the influence mechanism of the tip clearance on the flutter stability at different nodal diameters (ND), a series of compressor models were established with different tip clearances based on a transonic compressor rotor. The aerodynamic damping at each ND is obtained by influence coefficient method (ICM), while phase-shifted boundary method (PSB) is adopted to analyze the influence of the tip clearance on the flutter stability at different NDs. The results indicate the worst flutter stability for each tip clearance always appears at ND=1, where the aerodynamic damping exhibits a nonmonotonic trend of increasing first and decreasing thereafter along with the rising tip clearance. Two kinds of action are exerted by the tip clearance flow on the flow structures to alter the flutter stability: one is the tip clearance vortices which is generated on the suction side and impinge on the pressure side; the other is the interference of tip clearance vortices to the shock wave and to the flow separation. Besides, the influence of the changing aerodynamic coupling effect makes the above action bring about more drastic fluctuations to the unsteady pressure. At larger NDs, the unsteady pressure amplitude and phase fluctuate more sharply for larger tip clearances. Therefore, diverse change trends of the aerodynamic damping with the increasing tip clearance appear at different NDs, while the impingement of tip clearance vortices on the adjacent pressure side has a constantly stabilizing effect at different NDs.

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Dominant duct azimuthal acoustic mode detection considering failed wall-installed microphones with amplitude or phase measurement biases

Zhang,

Huang,

et al. 2024

Applied Acoustics

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Experimental investigation of aeroelastic instabilities in an aeroengine fan: Using acoustic measurements

Cited by 8 publications

References 29 publications

A Review on the High Sound Pressure Level Acoustic Measurement in the Aerospace Field

A Review on the High Sound Pressure Level Acoustic Measurement in the Aerospace Field

Influence mechanism of tip clearance on flutter stability with different aerodynamic coupling effects for transonic compressor

Dominant duct azimuthal acoustic mode detection considering failed wall-installed microphones with amplitude or phase measurement biases

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