摘要
将动态压缩系统模型应用于某型双转子发动机的高压压气机中。基于逐级特性，分析了高压压气机在进口平面温度突升条件下的动态响应及气动稳定性，进一步确定了进口温度突升条件下轴流压缩系统的失稳判别准则，并给出了高压压气机失稳的首发级。
he application of dynamic compression system model to a high pressure compressor indual axial jet engine is presented. The resulting systems of hyperbolic partial differential equations aresolved by the method of characteristics. Based on a set of stage-by-stage characteristics, theaerodynamic stability and unsteady response of the high pressure compressor to rapid inlettemperature ramps are given. A criterion for predicting aerodynamic stability limit in multi-stage axialcomplession systems with inlet planar temperature fluctuations is established. The first stage in whichthe flow instabilities occur is found using this criterion.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1996年第5期48-51,共4页
Journal of Propulsion Technology
基金
航空科学基金
关键词
航空发动机
轴流式
压缩机
Aircraft engine, Axial flow compressor,Aerodynamic stability,Stability criteria
