Aerodynamic performance matching of continuous transonic wind tunnel and its driving compressor

被引：0

作者：

Lei P. ^{[1
]}

Zhou E. ^{[1
,2
]}

Hu Y. ^{[1
]}

机构：

[1] High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang

[2] College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2021年 / 36卷 / 02期

关键词：

Aerodynamic performance; Axial compressor; Continuous wind tunnel; Safety operation; Surge margin;

D O I：

10.13224/j.cnki.jasp.2021.02.002

中图分类号：

学科分类号：

摘要：

In continuous transonic wind tunnel, performance matching between compressor and wind tunnel was essential for operation safety and efficiency. The aerodynamic performances of compressor and wind tunnel at different operation conditions were analyzed. Result showed that, at subsonic condition, operation of compressor was rather safe, with low risk of surge. At transonic or supersonic condition, slight variation of tunnel loss had no influence on compressor operation, while sharp rise of tunnel loss can cause supersonic flow in test section breakdown, and may induce compressor stall and impact of shock wave on model. To increase the safety of compressor, sufficient pressure ration margin and reasonable flow surge margin should be considered at design stage. © 2021, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：233 / 239

页数：6

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