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.
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
关键词
分级燃烧
液体火箭发动机
涡轮
staged combustion
liquid rocket engine
turbine
