一种新型压气机叶片造型方法的平面叶栅试验验证  

Verification of an Innovative Blading Method by Planar Cascade Test

作　　者：安利平[1] 李清华[1] 刘剑鹏[1] 马昌友[1] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500

出　　处：《燃气涡轮试验与研究》2013年第5期12-15,49,共5页Gas Turbine Experiment and Research

摘　　要：为验证一种新型超/跨声压气机叶片造型方法——B样条控制中线角叶型、贝塞尔曲线控制叶型厚度方法 (BMAA方法)的有效性,分别与原有的可控扩散叶型定制造型和任意中线造型进行平面叶栅对比试验。结果表明,BMAA方法得到的跨声叶型,具有比定制叶型更优的气动性能;BMAA方法得到的超声叶型,具有与任意中线叶型相似的气动性能;与传统叶片造型方法相比,BMAA方法具有更高的效率,可提高叶片的气动负荷。The advantage and feasibility of a newly developed blade modeling method （BMAA） was validat- ed by a planar cascade test compared with the former CDA method and the arbitrary camber lines method. The test results show that the transonic blade generated by the new method achieved better aerodynamic performance than CDA method; and the performance of supersonic blade is equal to that of arbitrary camber lines; the blade generated by the new method have higher efficiency and blade aerodynamic load which are superior to the conventional blade.

关 键 词：超 跨声压气机 高负荷叶型 叶片造型方法 B样条控制中线角叶型 任意中线叶型 定制叶型 平面叶栅试验 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]