关键词: 航空发动机;轴流式压缩机;气动稳定性;稳定性判据

Abstract: 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.

Key words: Aircraft engine;Axial flow compressor;Aerodynamic stability;Stability criteria