Investigation of aspirated compressor cascade flow fields using numerical simulation method

ZHOU Zheng-gui; WANG Chuan-bao

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Investigation of aspirated compressor cascade flow fields using numerical simulation method

更新时间：2026-07-07

- Investigation of aspirated compressor cascade flow fields using numerical simulation method
- Vol. 22, Issue 12, (2007)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院,南京,210016
  2. 中国航空工业第一集团公司, 沈阳发动机设计研究所,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2007
- 稿件说明：
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ZHOU Zheng-gui, WANG Chuan-bao. Investigation of aspirated compressor cascade flow fields using numerical simulation method[J]. 2007, 22(12).
DOI：

ZHOU Zheng-gui, WANG Chuan-bao. Investigation of aspirated compressor cascade flow fields using numerical simulation method[J]. 2007, 22(12). DOI：

摘要

为考察附面层吸附技术在压气机静子势流区叶型上的应用

采用流场数值计算方法对吸气叶栅流场进行模拟.结果表明:(1)对于高亚声速压气机叶栅

采用吸力面附面层吸除可提高叶栅的扩压度

但不一定能减小流动损失.(2)对于中亚声压气机叶栅

采用吸力面附面层吸除不仅可提高叶栅的扩压度而且能减小流动损失.(3)如果叶片吸力面靠后缘处有流动分离

吸气位置在分离区的上游较远处可抑制分离

若在分离区附近可能不利于抑制流动分离.

Abstract

To explore the application of boundary layer aspiration technology in compressor stator blade profiles of potential regions

the cascade flow fields were simulated numerically.The results indicate that:(1) for high subsonic inlet flow

the boundary layer in blade suction surface being aspirated can increase the cascade pressure rate and flow turning angle

but not always reduce flow loss;(2) for middle subsonic inlet flow

the boundary layer in blade suction surface being aspirated can increase the cascade pressure rate

flow turning angle and reduce flow loss;(3) if there is flow separation region in rear part of blade suction surface

the aspiration position located upstream far from the region can eliminate flow separation;but the separation region can not be eliminated if the aspiration position is near or within the region.

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Related Author

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Related Institution

The Engineering Institute, Air Force Engineering University

Science and Technology on Plasma Dynamics Laboratory, Aeronautics and Astronautics Engineering College, Air Force Engineering University

Institute of Engineering Thermophysics, Chinese Academy of Sciences

National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics

Laboratory of Propulsion System, The Engineering Institute, Airforce Engineering University

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