航空发动机
航空髮動機
항공발동궤
AERO ENGINE
2011年
5期
49-52
,共4页
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
軸流壓氣機%級特性%總壓畸變%失速首髮級%有效相對氣流角%航空髮動機
축류압기궤%급특성%총압기변%실속수발급%유효상대기류각%항공발동궤
axial flow compressor%stage characteristics%total pressure distortion%first stall stage%effective relative air-flow angle%aeroengine
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。
基于多級軸流壓氣機的逐級特性，髮展瞭1種預測週嚮總壓畸變條件下多級軸流壓氣機失速首髮級的方法。該方法結閤平行壓氣機模型和級疊加計算方法，以進氣畸變條件下多級軸流壓氣機某級的有效相對氣流角達到穩定狀態時該級的最大相對氣流角為條件，進行多級軸流壓氣機失速首髮級的預測分析。通過對J85—13髮動機8級軸流壓氣機總壓畸變試驗數據進行模擬計算，預測齣該軸流壓氣機畸變條件下的失速首髮級。
기우다급축류압기궤적축급특성，발전료1충예측주향총압기변조건하다급축류압기궤실속수발급적방법。해방법결합평행압기궤모형화급첩가계산방법，이진기기변조건하다급축류압기궤모급적유효상대기류각체도은정상태시해급적최대상대기류각위조건，진행다급축류압기궤실속수발급적예측분석。통과대J85—13발동궤8급축류압기궤총압기변시험수거진행모의계산，예측출해축류압기궤기변조건하적실속수발급。
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.
