海军航空工程学院学报Issue(3)：241-247,7.DOI:10.7682/j.issn.1673-1522.2015.03.008
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
贺孝涛 1闫庆安2
作者信息
- 1. 海军装备部
- 2. 西安航空动力股份有限公司，西安710021
- 折叠
摘要
Abstract
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Key words
compressor blade/leading edge geometry/engine performance/numerical simulation分类
航空航天引用本文复制引用
贺孝涛,闫庆安..某型发动机压气机叶片对性能的影响分析[J].海军航空工程学院学报,2015,(3):241-247,7.
