分级燃烧循环液体火箭发动机涡轮叶栅设计  

Design of Staged Combustion LRE Turbine Cascade

作　　者：李斌[1] 韩飞[2] 陈本森[2] 张贵田[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]航天六院11所,陕西西安710100

出　　处：《燃气涡轮试验与研究》2008年第4期46-51,共6页Gas Turbine Experiment and Research

摘　　要：本文利用涡轮设计软件,设计了用于分级循环燃烧火箭发动机的涡轮叶栅。为控制二次流损失,动静叶均采用先进的后加载叶型,静子叶栅采用正弯设计。流场计算结果表明,弯曲静叶整级效率提高0.92%,静叶内部漩涡强度减小,二次流减弱。经涡轮吹风试验验证,其级性能完全满足要求。这也表明后加载叶型及叶片正弯的方法适用于该类型涡轮。Turbine cascade used for staged combustion LRE was designed by using turbine design software. In order to control secondary flow loss, stator and rotor cascade were aft-loaded, stator blade was positive curved. Analysis of ＇flow field indicated an efficiency increasing of 0.92% and also decreasing of inside eddy of stator and secondary flow. The experiment results showed that the aerodynamic performance was satisfied. It was proved that the aft-loaded and positive curved design concepts were applicable for this type of turbine.

关 键 词：分级燃烧 液体火箭发动机 涡轮 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]