Numerical Investigation on the Response of End-Wall Flow to Inlet Total Pressure Distortion in Axial Compressor

doi:10.7652/xjtuxb202005008

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Numerical Investigation on the Response of End-Wall Flow to Inlet Total Pressure Distortion in Axial Compressor

更新时间：2025-07-09

- Numerical Investigation on the Response of End-Wall Flow to Inlet Total Pressure Distortion in Axial Compressor
- Vol. 54, Issue 5, Pages: 53-60(2020)
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202005008
  CLC： TH137.52
- Online First：10 May 2020，
  
  Published：2020
- 稿件说明：
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Numerical Investigation on the Response of End-Wall Flow to Inlet Total Pressure Distortion in Axial Compressor[J]. 2020, 54(5): 53-60.
DOI：

Numerical Investigation on the Response of End-Wall Flow to Inlet Total Pressure Distortion in Axial Compressor[J]. 2020, 54(5): 53-60. DOI： 10.7652/xjtuxb202005008.

摘要

为了探究进口周向总压畸变对压气机性能的影响

以及不同畸变角下压气机端区流场对畸变响应的区别

对跨声速轴流压气机一级动静叶进行全周非定常数值模拟

分别采用均匀来流

畸变角为30°、90°和120°的畸变来流这4种进口条件。进口畸变使压气机的性能明显恶化

并且随着畸变角的增大恶化加剧。畸变角为120°时

随着动叶扫过畸变区

动叶叶顶区域激波的结构和强度发生改变

叶顶间隙泄漏涡的轨迹和强度也发生周期性变化。畸变也会对下游静叶流动产生影响

使静叶叶顶和角区分离加重。当畸变角为90°时

所影响的动叶流道数减少但流场对畸变的响应规律没变。当畸变角减小到30°时

畸变经过动叶完全衰减

静叶流场几乎不受影响。研究结果揭示了压气机性能改变和叶顶、叶根端区流动结构动态特征与畸变来流间的关系

可为提高压气机抗畸变能力提供理论基础。

Abstract

To study the effect of the inlet circumferential total pressure distortion on the compressor performance

as well as the difference in the responses of end-wall flow to the inlet distortion under different distortion angles

annulus unsteady numerical simulations are performed on the first stage of a transonic axial compressor. A uniform inlet flow and three distorted flows with the distortion angles of 30-

90- and 120- are adopted as the inlet conditions. Simulation results show that the inlet distortion significantly worsens the compressor performance

and the performance deterioration increases with the distortion angle. When the distortion angle is 120-

the structure and strength of the shock waves in the tip region of blades will change as the rotor blade sweeps through the distortion region

and the trajectory and strength of the tip clearance leakage vortexes also fluctuate periodically. The distortion also affects the flow in the downstream stator blades and aggravates th

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references

KOFF B L. Gas turbine technology evolution: a designer’s perspective [J]. Journal of Propulsion and Power, 2004, 20(4): 577-595.

FIDALGO V J, HALL C A. A study of fan-distortion interaction within the NASA Rotor 67 transonic stage [J]. Journal of Turbomachinery, 2012, 14(5): 1-8.

PAGE J H, HIELD P, TUCKER P G. Effect of inlet distortion features on transonic fan rotor stall [J]. Journal of Turbomachinery, 2018, 140(7): 1008-1019.

ZORI L, GALPIN P, CAMPREGHER R, et al. Time-transformation simulation of a 1.5 stage transonic compressor [J]. Journal of Turbomachinery, 2017, 139(7): 3-8.

REID C. The response of axial flow compressors to intake flow distortion [C]∥ ASME 1969 Gas Turbine Conference and Products Show. New York, USA: ASME, 1969: 29-43.

SANGER N L. Performance of a 1.57 pressure-ratio transonic fan stage with a screen-induced 90 deg circumferential inlet flow distortion: NASA TN-D8163 [R]. Cleveland, USA: NASA, 1975: 7-17.

COLPIN J, KOOL P. Experimental study of an axial compressor rotor transfer function with non-uniform inlet flow [C]∥ ASME 1978 International Gas Turbine Conference and Products Show. New York, USA: ASME, 1978: 69-78.

DATKO J T, O’HARA J A. The aeromechanical response of an advanced transonic compressor to inlet distortion [C]∥ ASME 1987 International Gas Turbine Conference and Exhibition. New York, USA: ASME, 1987: 189-200.

ZHANG W Q, VAHDATI M. A parametric study of the effects of inlet distortion on fan aerodynamic stability [J]. Journal of Turbomachinery, 2019, 141(1): 1212-1223.

GIULIANI J E, CHEN J P. Fan response to boundary-layer ingesting inlet distortions [J]. AIAA Journal, 2016, 54(10): 3232-3243.

孙鹏, 高海洋, 钟兢军. 总压畸变对超声速压气机动叶端区流场结构的影响 [J]. 推进技术, 2013, 34(6): 747-753.

SUN Peng, GAO Haiyang, ZHONG Jingjun. Effects of total pressure distortion on rotor end wall flow structure of a supersonic compressor [J]. Journal of Propulsion Technology, 2013, 34(6): 747-753.

高海洋, 孙鹏, 钟兢军. 总压畸变对跨声速压气机静叶端区流场结构影响研究 [J]. 推进技术, 2014, 35(5): 641-647.

GAO Haiyang, SUN Peng, ZHONG Jingjun. Effects of total pressure distortion on stator end-wall flow structure of a transonic compressor [J]. Journal of Propulsion Technology, 2014, 35(5): 641-647.

GUNN E J, HALL C A. Aerodynamics of boundary layer ingesting fan [C]∥ ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. New York, USA: ASME, 2014: 24-37.

SUN P, FU W G. Numerical research on inlet total pressure distortion in a transonic compressor with non-axisymmetric stator [J]. Journal of Aerospace Engineering, 2019, 233(2): 667-678.

徐文峰. 非轴对称静叶间隙对畸变条件下压气机流场影响的数值研究 [D]. 大连: 大连海事大学, 2018: 1-7.

STRAZISAR A J, WOOD J R, HATHAWAY M D, et al. Laser anemometer measurements in a transonic axial-flow compressor rotor: NASA technical paper 2879 [R]. Cleveland, Ohio, USA: Lewis Research Center, 1989.

余春华, 李秋实, 袁巍, 等. 进口畸变下非定常数值模拟进口边界数学模型 [J]. 航空动力学报, 2008, 23(9): 1695-1700.

YU Chunhua, LI Qiushi, YUAN Wei, et al. Boundary condition model for unsteady numerical simulation under inlet distortion [J]. Journal of Aerospace Power, 2008, 23(9): 1695-1700.

GOVARDHAN M, VISWANATH K. Investigations on an axial flow fan stage subjected to circumferential inlet flow distortion and swirl [J]. Journal of Thermal Science, 1997(4): 241-250.

尹超, 金海良, 银越千. 进气畸变下压气机过失速三维非定常模型探索 [J]. 航空动力学报, 2018, 33(6): 1393-1402.

YIN Chao, JIN Hailiang, YIN Yueqian. Exploration of three-dimensional unsteady model for compressor post-stall under inlet distortion [J]. Journal of Aerospace Power, 2018, 33(6): 1393-1402.

MANWARING S R, FLEETER S. Inlet distortion generated periodic aerodynamic rotor response [J]. Journal of Turbomachinery, 1990, 112(2): 298-307.

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