摘要
针对某型航空发动机的风扇叶轮采用直纹叶片造型的方法实施改型气动设计、全三维数值模拟和试验,以达到提高该风扇叶轮在该发动机巡航状态的性能.设计、计算和试验结果表明改型风扇叶轮达到了设计指标,可为类似的风扇/压气机改型设计提供借鉴.
An aerodynamic redesign for a fan stage which uses ruled blade design method is conducted in this paper,in order to improve the performance of the stage when the turbofan engine works at the cruise state.By through-flow inverse calculation,three dimensional numerical simulation and experiment validation,the redesign has achieved its main object,and could be referenced by similar fan/compressor redesign procedure.
出处
《战术导弹技术》
2010年第1期81-85,共5页
Tactical Missile Technology
关键词
风扇级
改型设计
数值模拟
fan stage
redesign
numerical simulation
