不均匀进气对压缩系统稳定性影响的逐级动态响应模型研究

推进技术 ›› 1999, Vol. 20 ›› Issue (2): 56-60.

不均匀进气对压缩系统稳定性影响的逐级动态响应模型研究

吴虎,廉小纯,陈辅群

西北工业大学航空动力与热力工程系;西北工业大学航空动力与热力工程系;西北工业大学航空动力与热力工程系

发布日期:2021-08-15

ON MODEL OF STAGE BY STAGE DYNAMIC BLADE RESPONSE FOR PREDICTING AERODYNAMIC STABILITIES IN MULTISTAGE AXIAL COMPRESSORS WITH INLET DISTORTIONS

Dept.of Aeroengine Engineering,Northwestern Polytechnical Univ ,Xi′an,710072;Dept.of Aeroengine Engineering,Northwestern Polytechnical Univ ,Xi′an,710072;Dept.of Aeroengine Engineering,Northwestern Polytechnical Univ ,Xi′an,710072

Published:2021-08-15

摘要/Abstract

摘要： 发展了一种分析进口畸变对多级轴流压气机影响的逐级动态响应模型。采用动态压缩系统模型和动态加载技术，建立了一种压缩系统气动稳定性分析的新方法。应用新的模拟方法对一８级跨声多级压气机进行了详细的数值分析。结果表明，所发展的逐级动态响应模型更合理和可靠。基于流动阻塞，给出了一种更为迅速的压缩系统失稳识别方法。

关键词: 航空发动机;轴流式压气机;气动稳定性;动态响应

Abstract: A new model was presented for pedicting the effects of inlet distortions on the aerodynamic stabilities in multistage axial compressors.The dynamic compression system model and dynamic loading were used.The predictions for a eight stage transonic compressor were given using this model.The numerical results show that this new model is both more reasonable and more reliable.Based on flow blockage a new parameter of determining flow instability was found.It is apparent that this parameter is a better early warning criterion of predicting the stage in which the flow instabilities occur

Key words: ircraft engine;Axial flow compressor;Aerodynamic stability;Dynamic response

吴虎,廉小纯,陈辅群. 不均匀进气对压缩系统稳定性影响的逐级动态响应模型研究[J]. 推进技术, 1999, 20(2): 56-60.