斜切口短舱进气道引发的稳态流动畸变随短舱缩短的设计趋势而加剧。为了探究斜切口短舱进气道是否会对压气机的特性和噪声产生影响，本文设计了一种斜切口进气道，进行了实验室压气机地面条件下的压气机实验。实验结果表明：针对本文的研究对象，斜切口进气道在远离风扇2.3倍管径距离时，几乎不影响风扇的压升及效率特性，也不会改变其失速起始模式。斜切口进气道出口声场的频谱特性和模态与标准进气道规律相似，而稳态流动畸变对转静干涉噪声存在干扰。模态结果表明，理论模型的预测不完全适用于本文的研究对象TA29试验台，同时斜切口进气道的不对称性，使前传至进气道的噪声模态在更多非主导模态上被激发或削弱。
The steady flow distortion induced by the drooped intakes intensifies with the design trend of shortening the nacelle length. To investigate whether drooped intakes impact compressor performance and noise, this study designed a drooped intake and con-ducted compressor experiments under static intake conditions. Experimental results demonstrate that for the subject investigated, at a distance of 2.3 times the duct diameters upstream of the fan, the drooped intake exerts negligible influence on fan pressure rise and efficiency characteristics and does not alter its stall inception pattern. The spectral characteristics and mode composi-tion of the exhaust sound field from the drooped intake align with those of standard intakes, while steady flow distortion perturbs rotor-stator interaction noise. Mode analysis reveals that theoretical modes are not fully applicable to the TA29 test rig examined herein. Additionally, the asymmetry of the drooped intake enhances or suppresses upstream-propagating noise modes across multiple non-dominant mode orders.
[1]TEJERO F, ROBINSON M, MACMANUS D G, et al.Multi-objective optimisation of short nacelles for high bypass ratio engines[J].Aerospace Science and Tech-nology, 2019, 91:410-421
[2]TEJERO F, MACMANUS D, SHEAF C.Impact of Droop and Scarf on the Aerodynamic Performance of Compact Aero-Engine Nacelles[C]//AIAA Scitech 2020 Forum. 2020.
[3]TEJERO F, CHRISTIE R, MACMANUS D, et al.Non-axisymmetric aero-engine nacelle design by sur-rogate-based methods[J].Aerospace Science and Technology, 2021, 117:-
[4]PETERS A, SPAKOVSZKY Z S, LORD W K, et al.Ultrashort Nacelles for Low Fan Pressure Ratio Pro-pulsors[J].Journal of Turbomachinery, 2015, 137(2):-
[5]JOO W G.Numerical Investigation of Installation Effects in Turbofan Engines[J].Journal of Propulsion and Power, 2000, 16(4):697-704
[6]JOO W G.Intake/engine flowfield coupling in turbo-fan engines[D]. 1994.
[7]BU H, HUANG X, ZHANG X.An overview of testing methods for aeroengine fan noise[J].Progress in Aero-space Sciences, 2021, 124:-
[8]SCHWALLER P, BAKER N, TOMLINSON D, et al.Noise Validation of Model Fan Rig with En-gine[C]//12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference). 2006.
[9]DOHERTY M, NAMGOONG H.Impact of Turbofan Intake Distortion on Fan Noise Propagation and Gen-eration[C]//22nd AIAA/CEAS Aeroacoustics Confer-ence. 2016.
[10]PRINN A, SUGIMOTO R, ASTLEY R J.The Effect of Steady Flow Distortion on Noise Propagation in Turbofan Intakes[C]//22nd AIAA/CEAS Aeroacous-tics Conference. 2016.
[11]WINKLER J, REIMANN C A, REBA R A, et al.Tur-bofan Inlet Distortion Noise Prediction with a Hybrid CFD-CAA Approach[C]//20th AIAA/CEAS Aeroa-coustics Conference. 2014.
[12]HERKES W, NESBITT E, CALLENDER B, et al.The Quiet Technology Demonstrator Program: Static Test of Airplane Noise-Reduction Concepts[C]//13th AIAA/CEAS Aeroacoustics Conference (28th AIAA Aeroacoustics Conference). Rome, Italy: American Institute of Aeronautics and Astronautics, 2007.
[13]LAN J, PREMO J, ZLAVOG G, et al.Phased Array Measurements of Full-Scale Engine Inlet Noise[C]//13th AIAA/CEAS Aeroacoustics Confer-ence (28th AIAA Aeroacoustics Conference). Rome, Italy: American Institute of Aeronautics and Astro-nautics, 2007.
[14]RADEMAKER E, SIJTSMA P, TESTER B.Mode detection with an optimised array in a model turbofan engine intake at varying shaft speeds[C]//7th AIAA/CEAS Aeroacoustics Conference and Exhibit. Maastricht, Netherlands: American Institute of Aero-nautics and Astronautics, 2001.
[15]ZHANG Y, DONG X, LI Z, et al.Numerical and Ex-perimental Investigation of Steady Flow Distortion in Drooped Turbofan Intakes[C]//GT2024 Volume 1: Aircraft Engine. 2024.
[16]李志彬, 王晓宇, 孙晓峰, 等.单级低速轴流压气机噪声特性实验研究[J].推进技术, 2018, 39(6):1275-1282
[17]王宇晴, 孙大坤, 李佳, 等.一种壁面处理对压气机性能影响的实验研究[J].工程热物理学报, 2023, 44(06):1511-1518
[18]XU D.Effect Mechanism of Blade Loading on Com-pressor Flow Stability[D]. Beijing, China: beihang university, 2022.
[19]MCDOUGALL N M, CUMPSTY N A, HYNES T P.Stall Inception in Axial Compressors[J].Journal of Turbomachinery, 1990, 112(1):116-123
[20]GARNIER V H, EPSTEIN A H, GREITZER E M.Rotating Waves as a Stall inception Indication in Axi-al Compressors[J].Journal of Turbomachinery, 1991, 113(2):290-301
[21]EFRON B.Bootstrap Methods: Another Look at the Jackknife[J].The Annals of Statistics, 1979, 7(1):1-26
[22]TYLER J M, SOFRIN T G.Axial Flow Compressor Noise Studies[C]//Pre-1964 SAE Technical Papers. 1962: 620532.
[23]SMITH E, MOORE M, GLIEBE P.Distortion-rotor interaction noise produced by a drooped inlet[C]//6th Aeroacoustics Conference. Hartford, CT, U.S.A.: American Institute of Aeronautics and Astronautics, 1980.
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