畸变进气下压缩系统稳定性分析的通用方法  

A GENERAL METHOD FOR PREDICTING AERODYNAMIC STABILITY IN MULTISTAGE AXIAL COMPRESSION SYSTEMS UNDER INLET FLOW DISTORTION

作　　者：吴虎[1] 廉小纯[1] 陈辅群 崔建勇 

机构地区：[1]西北工业大学航空动力与热力工程系,西安710072

出　　处：《推进技术》1997年第5期62-64,共3页Journal of Propulsion Technology

基　　金：航空科学基金

摘　　要：基于逐级平行压缩系统模型，发展了一种分析周向组合畸变对多级轴流压缩系统稳定性影响的通用分析方法。应用此方法对两个多级轴流压气机进行了详细的数值分析，给出了纯压力畸变、纯温度畸变及压力－温度不同位置的组合畸变与轴流压气机喘振裕度损失之间的定量关系。A general numerical method is developed for predicting aerodynamic stability inmultistage axial compression systems with inlet combined pressure and temperature distortion basedon stage-by-stage parallel compression system model. The predictions for two multistage axial flowcompressors are given by using this method. The quantitative relationships between the inlet totalpressure distortion, or total temperature distortion, or combined pressure and temperature distortionand the surge margin losses are obtained. It is found that the effects of aligned pressure andtemperature distortion on aerodynamic stability of axial compressors are the most strong.

关 键 词：压气机 进气道畸变 畸变进气 气动稳定性 稳定性 

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] V231.3