航空发动机涡轮动叶设计平台的构建与验证  

Establishment and Verification of Aeroengine Turbine Rotor Blade Design Platform

作　　者：李磊[1] 敖良波[1] 王心美[1] 岳珠峰[1] 

机构地区：[1]西北工业大学工程力学系,西安710129

出　　处：《航空发动机》2012年第3期24-28,共5页Aeroengine

基　　金：博士后基金(20100471634);863计划(2009AA04Z418)资助

摘　　要：针对航空发动机涡轮叶片的设计流程,开发了涡轮动叶的设计平台。基于气动热力学方法建立了1维性能设计模块;并在研究平面叶栅造型设计方法的基础上,建立了2维气动分析模块,可以实现2维叶型气动性能的快速分析;在实心/冷却叶片参数化设计的基础上,引入多学科可行方法,建立了实心/冷却叶片设计和多学科优化模块。利用所开发的设计平台进行了某型冷却叶片的多学科设计优化,有效提高了该叶片的综合性能,验证了平台的有效性。Aiming at design process of aeroengine turbine rotor blade, its platform was developed. One-dimensional performance design module was developed with aerothermodynamics. Based on planar cascade method, the two-dimensional aerodynamic design module which can predict the performance of the cascade quickly was built. The cooling blade and multi-disciplinary design optimization module were built with multi-disciplinary method based on the cooling blade parametric design. The multi-disciplinary design optimization of a cooling blade was obtained by the design platform, which effectively improve the blade integrated performance and validate the platform efficiency.

关 键 词：航空发动机 涡轮叶片 设计平台 设计流程 多学科设计优化 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]