某型发动机压气机叶片对性能的影响分析  

Inpact Analysis A Certain Type of Engine Compressor Blade on Performance Analysis

作　　者：贺孝涛[1] 闫庆安 

机构地区：[1]海军装备部 [2]西安航空动力股份有限公司,西安710021

出　　处：《海军航空工程学院学报》2015年第3期241-247,共7页Journal of Naval Aeronautical and Astronautical University

摘　　要：采用CFD数值模拟方法和厂内试车方法,对某型发动机压气机叶片设计状态(A状态)和产品实际情况(B状态,转接半径、叶型厚度偏离较大)下,叶片前缘形状对发动机性能的影响进行了分析和试车验证,结果表明:B状态叶片,气流沿叶型整个型面附面层厚度呈迅速增大趋势,在较大区域较早出现气流分离,易导致压气机处于非稳定性状态工作;试车结果表明其导致整机推力性能降低。In this paper, CFD numerical simulation method and plant test methods for a certain type of engine compressor blade design state （state A） and lower （state B, transfer radius, thickness deviation larger leaf type） products, the actual sit- uation, the shape of the blade leading edge impact on engine performance was analyzed and validated test results showed that, state B leaves leaf type airflow along the entire profile of the boundary layer thickness was rapidly increasing trend in the earlier onset of flow separation larger area, easily lead to compressor the stability of the state in a non-working; it leads to lower test results showed that the whole thrust performance.

关 键 词：压气机叶片 前缘形状 发动机性能 数值模拟 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]