轴流压气机进口总压畸变的端区流动响应数值研究

匡也; 王志恒; 李雨润; 席光

doi:10.7652/xjtuxb202005008

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轴流压气机进口总压畸变的端区流动响应数值研究

更新时间：2025-07-09

- 轴流压气机进口总压畸变的端区流动响应数值研究
- Numerical Investigation on the Response of End-Wall Flow to Inlet Total Pressure Distortion in Axial Compressor
- 西安交通大学学报 2020年54卷第5期页码：53-60
- 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：
  
  : 2019-10-29。作者简介: 匡也(1996—),女,硕士生;王志恒(通信作者),男,副教授。基金项目: 国家科技重大专项资助项目(2017-II-0004-0016)
- DOI：10.7652/xjtuxb202005008
  中图分类号： TH137.52
- 网络首发：2020-05-10，
  
  纸质出版：2020
- 稿件说明：
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匡也, 王志恒, 李雨润, 等. 轴流压气机进口总压畸变的端区流动响应数值研究[J]. 西安交通大学学报, 2020,54(5):53-60.

Numerical Investigation on the Response of End-Wall Flow to Inlet Total Pressure Distortion in Axial Compressor[J]. 2020, 54(5): 53-60.
匡也, 王志恒, 李雨润, 等. 轴流压气机进口总压畸变的端区流动响应数值研究[J]. 西安交通大学学报, 2020,54(5):53-60. DOI： 10.7652/xjtuxb202005008.

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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