摘要
基于多级轴流压气机的逐级特性,发展了1种预测周向总压畸变条件下多级轴流压气机失速首发级的方法。该方法结合平行压气机模型和级叠加计算方法,以进气畸变条件下多级轴流压气机某级的有效相对气流角达到稳定状态时该级的最大相对气流角为条件,进行多级轴流压气机失速首发级的预测分析。通过对J85-13发动机8级轴流压气机总压畸变试验数据进行模拟计算,预测出该轴流压气机畸变条件下的失速首发级。
Based on the miltistage axial flow compressor characteristics,a method was developed for predicting first stall stage of multistage axial flow compressors with circumferential total pressure distortion. By parallel compressor model and stage-stacking method, prediction of first stall stage for multistage axial compressure was made with a stage maximum relative air-flow on the condition that effective relative air-flow angle of the stage for multistage axial flow compressors with circumferential pressure distortion was equal to the angle without distortion. The first stall stage of J85-13 engine eight stage axial flow compressor with distortion was predicted with the numerical simulation of its total pressure distortion test data.
出处
《航空发动机》
2011年第5期49-52,共4页
Aeroengine
关键词
轴流压气机
级特性
总压畸变
失速首发级
有效相对气流角
航空发动机
axial flow compressor
stage characteristics
total pressure distortion
first stall stage
effective relative air-flow angle
aeroengine
