一种分析稳态压力畸变对多级轴流压缩系统稳定性影响的新方法  

A NEW METHOD FOR PREDICTING AERODYNAMICSTABILITY OF MULTLI-STAGE AXIAL COMPRESSORSYSTEM WITH INLET STEADY PRESSURE DISTORTION

作　　者：吴虎[1] 廉小纯[1] 陈辅群[1] 

机构地区：[1]西北工业大学航空发动机系

出　　处：《推进技术》1996年第1期42-46,共5页Journal of Propulsion Technology

基　　金：航空科学基金

摘　　要：发展了一种分析进口稳态压力畸变对多级轴流压缩系统稳定性影响的逐级平行压缩系统模型；建立了一种稳态压力畸变进气条件下，多级轴流压缩系统对燃烧室燃油瞬时脉冲的气动响应及气动稳定性分析的新方法；导出了基于ＭａｃＣｏｒｍａｃｋ隐式格式的新的数值计算方法。应用新的模型方法对一个三级实验压气机进行了数值分析，给出了稳态压力畸变与压缩系统稳定裕度损失及不稳定发生时间之间的定量关系，定量给出了压气机失稳首发级的识别方法。stage-by-stage parallel compression system model for predicting aerodynamic stability of multi-stage axial compressor system with inlet steady pressure distortion is presented in this paper. A new model for simulating the effect of fuel injection oscillation in burner on the performanceand aerodynamic stability of the multi-stage axial compressor system with inlet steady pressure distortion is established. Based on MacCOrmack's implicit scheme, a new numerical method is developed.The predictions for a three-stage experimental axial compressor are given by using this new model.The quantitive relationships between the inlet total pressure distortion and the surge margin losses orthe time to surge are obtained. The third stage in which the flow instabilities occur is indicated by using the quantitive criterion.

关 键 词：轴流式 压缩机 气动稳定性 进气道畸变 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]