一种斜切口进气道对压气机性能的影响

doi:10.7527/S1000-6893.2025.32676

Abstract

Abstract:

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 conducted 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 composition 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 experiment rig examined herein. Additionally， the asymmetry of the drooped intake enhances or suppresses upstream-propagating noise modes across multiple non-dominant mode orders.

Key words: compressor/fan, intake, intake/engine compatibility, fan noise, acoustic mode

CLC Number:

V231.3

Yuhan ZHANG, Lei FU, Ruoyang LIU, Ning MA, Ming ZHANG, Xu DONG, Zhenyu LI, Dakun SUN, Xiaofeng SUN. Effect of a drooped intake on performance of compressor[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(7): 632676.

Figures/Tables 16

Fig.1

Fig.2

Table 1

Fig.3

Fig.4

Fig.5

Fig.6

Table 2

Uncertainties of experimental measurements

参数	数值
流量系数不确定度 $u φ$	0.001 44
流量系数参考值 $φ r e f$	0.467
流量系数相对误差 $u φ φ r e f$ /%	0.309
静压升系数不确定度 $u ψ$	0.003 42
静压升系数参考值 $ψ r e f$	0.46
静压升系数相对误差 $u ψ ψ r e f$ /%	0.744

Table 2

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Table 3

In-duct circumferential mode analysis

BPF	k	m=nB+kV	$f m n c / H z$	$Ω c u t - o f f /$ （r·min^-1）
1	-1	-4	1 918.3	5 004
2	-1	19	7 641.5	9 967
	-2	-8	3 480.3	4 540
3	-2	15	6 140.1	5 339
	-3	-12	5 006.8	4 354
4	-3	11	4 627.2	3 018
	-4	-16	6 516.3	4 250
5	-4	7	3 094.5	1 615
6	-5	3	1 515.6	659

Table 3

Fig.12

Table 4

Sound pressure level at theoretically predicted acoustic modes of rotor-stator interaction

BPF	m=nB+kV	$S T D / d B$	$S L / d B$
1	-4	118.7	118.8
2	19（1）	截止	截止
	-8	96.1	97.3
3	15（-3）	113.8	113.0
	-12（-6）	96.4	97.0
4	11（-7）	98.7	97.0
	-16（2）	95.4	94.9
5	7	83.2	83.5
6	3	81.9	79.7

Table 4

References 24

[1]	MAO Y B， DANG T Q. A three-dimensional body-force model for nacelle-fan systems under inlet distortions［J］. Aerospace Science and Technology， 2020， 106： 106085.
[2]	JOO W G. Numerical investigation of installation effects in turbofan engines［J］. Journal of Propulsion and Power， 2000， 16（4）： 697-704.
[3]	FERNANDO T， DAVID M M， CHRISTOPHER S.Impact of droop and scarf on the aerodynamic performance of compact aero-engine nacelles［C］∥AIAA Scitech 2020 Forum. Reston： AIAA， 2020.
[4]	PETERS A， SPAKOVSZKY Z S， LORD W K， et al. Ultrashort nacelles for low fan pressure ratio propulsors［J］. Journal of Turbomachinery， 2015， 137（2）： 021001.
[5]	JOO W G. Intake/engine flowfield coupling in turbofan engines［D］. Cambridge： University of Cambridge， 1994.
[6]	CAO T， VADLAMANI N R， TUCKER P G， et al. Fan-intake interaction under high incidence［J］. Journal of Engineering for Gas Turbines and Power， 2017， 139（4）： 041204.
[7]	BU H X， HUANG X， ZHANG X. An overview of testing methods for aeroengine fan noise［J］. Progress in Aerospace Sciences， 2021， 124： 100722.
[8]	SCHWALLER P， BAKER N， TOMLINSON D， et al. Noise validation of model fan rig with engine［C］∥12th AIAA/CEAS Aeroacoustics Conference （27th AIAA Aeroacoustics Conference）. Reston： AIAA， 2006.
[9]	DOHERTY M， NAMGOONG H. Impact of turbofan intake distortion on fan noise propagation and generation［C］∥22nd AIAA/CEAS Aeroacoustics Conference. Reston： AIAA， 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 Aeroacoustics Conference. Reston： AIAA， 2016.
[11]	WINKLER J， REIMANN C A， REBA R A， et al. Turbofan inlet distortion noise prediction with a hybrid CFD-CAA approach［C］∥20th AIAA/CEAS Aeroacoustics Conference. Reston： AIAA， 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）. Reston： AIAA， 2007.
[13]	LAN J， PREMO J， ZLAVOG G， et al. Phased array measurements of full-scale engine inlet noise［C］∥13th AIAA/CEAS Aeroacoustics Conference （28th AIAA Aeroacoustics Conference）. Reston： AIAA， 2007.
[14]	Mode detection with an optimised array in a model turbofan engine intake at varying shaft speeds［C］∥7th AIAA/CEAS Aeroacoustics Conference and Exhibit. Reston： AIAA， 2001.
[15]	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.
	LI Z B， WANG X Y， SUN X F， et al. Experimental research on noise of single-stage low-speed axial compressor［J］. Journal of Propulsion Technology， 2018， 39（6）： 1275-1282 （in Chinese）.
[16]	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（6）： 1511-1518.
	WANG Y Q， SUN D K， LI J， et al. Experimental study of a novel casing treatment on the performance of compressors［J］. Journal of Engineering Thermophysics， 2023， 44（6）： 1511-1518 （in Chinese）.
[17]	ZHANG Y H， DONG X， LI Z Y， et al. Numerical and experimental investigation of steady flow distortion in drooped turbofan intakes［C］∥ASME Turbo Expo 2024： Turbomachinery Technical Conference and Exposition. New York： ASME， 2024.
[18]	许登科. 压气机流动稳定性中叶片负荷影响机制研究［D］. 北京：北京航空航天大学， 2022.
	XU D K. Effect mechanism of blade loading on compressor flow stability［D］. Beijing： Beihang University， 2022 （in Chinese）.
[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 axial compressors［J］. Journal of Turbomachinery， 1991， 113（2）： 290-301.
[21]	ABERNETHY R B， BENEDICT R P， DOWDELL R B. ASME measurement uncertainty［J］. Journal of Fluids Engineering， 1985， 107（2）： 161-164.
[22]	EFRON B. Bootstrap methods： Another look at the jackknife［J］. The Annals of Statistics， 1979， 7（1）： 1-26.
[23]	TYLER J M， SOFRIN T G. Axial flow compressor noise studies： 620532 ［R］. Warrendale： SAE， 1962.
[24]	SMITH E， MOORE M T， GLIEBE P. Distortion-rotor interaction noise produced by a drooped inlet［C］∥6th Aeroacoustics Conference. Reston： AIAA， 1980.

类别	参数	数值
类别	参数	静子	转子
几何参数	叶片数	23	27
	流道外径/mm	300	300
	展弦比	1.2	1.4
	轮毂比	0.61	0.61
	叶尖间隙/mm		0.40
	转静间隙/mm	30~35
气动设计参数	设计流量/（kg·s^-1）	2.90
	设计转速/（r·min^-1）	5 800
	功率/kW	9.568 7
	设计效率	0.864
	设计压升	1.031
	转子叶中速度/（m·s^-1）	72.88

Effect of a drooped intake on performance of compressor

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 16

References 24

Related Articles 14

Recommended Articles

Metrics

Comments

[1]	Dongfei ZHANG, Junhui GAO. High-precision numerical simulation of fan rotor-stator interaction pure tone [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(7): 130884-130884.
[2]	Dongfei ZHANG, Junhui GAO. Application of GPU⁃accelerated high⁃order spectral difference method in fan noise [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 128941-128941.
[3]	Bi WEN, Baijie QIAO, Zepeng LI, Zhendong LI, Yanfeng WANG, Xuefeng CHEN. Synchronous vibration identification of fan blisk based on acoustic mode decomposition [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 227066-227066.
[4]	Zhiyuan XU, Mingsui YANG, Meng WANG. Theoretical prediction and experimental study on acoustic resonance characteristics of certain type of compressor [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628236-628236.
[5]	BAI Keqiang, ZHANG Song, DAN Zhihong, QIAN Qiumeng. Noise suppression method of intake pressure control system for aircraft engine [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125779-125779.
[6]	YAN Qun, XUE Dongwen, GAO Xiang, YANG Jiafeng, HUANG Wenchao. Acoustic performance experimental technology of aircraft nacelle acoustic liner [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 526810-526810.
[7]	XIE Xiaole, LI Jiyuan, WANG Xian, LU Haifeng, HAN Xianwei. Influence of air-intake structure in air-breathing electric propulsion system on intake performance [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 125272-125272.
[8]	ZHAO Zhenshan, FENG Jian, MIAO Shuming, DU Yu. Blended-wing-body aircraft overhanging engine layout technology based on numerical simulation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(9): 623051-623051.
[9]	ZHANG Weiguang, WANG Xiaoyu, SUN Xiaofeng. Passive control of fan noise by vane sweep and lean [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(2): 120265-120273.
[10]	XIE Xue-ming;GUO Rong-wei. Experimental Research on RCS of Bump Inlet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2006, 27(2): 193-197.
[11]	YANG Ai-ling;GUO Rong-wei. NUMERICAL SIMULATION OF THE FLOW OF TWO-DIMENSIONAL SUBMERGED AIR INTAKE [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1999, 20(5): 450-454.
[12]	Weng Peifen;Zhou Zhewei;Guo Rongwei. CALCULATIONAL AND EXPERIMENTAL INVESTIGATION ON FLOW FIELD FOR A SUBMERGED AIR INLET [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1996, 17(S1): 125-128.
[13]	Huang Tao;Zhao Minggui. RESEARCH OF EM SCATTERING OF JET ENGINE INTAKES USING SHOOTING AND BOUNCING RAYS APPROACH [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1995, 16(1): 99-104.
[14]	Huang Mingke. AN EFFICIENT FINITE-DIFFERENCE ALGORITHM FOR COMPUTING AXISYMMETRIC TRANSONIC NACELLE FLOW FIELDS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1990, 11(1): 1-6.