大叶顶间隙高效率火箭发动机涡轮设计  

Design of High Efficiency Turbine with Large Tip Clearance for Rocket Engine

作　　者：李斌[1] 王晓锋[2] 陈本森[2] 张贵田[1] 

机构地区：[1]西北工业大学,西安710072 [2]西安航天动力研究所,西安710100

出　　处：《宇航学报》2009年第2期695-698,共4页Journal of Astronautics

摘　　要：补燃循环液体火箭发动机富氧燃气涡轮叶顶间隙大的特点,导致损失很大。为了提高效率,设计中采取了低的级反力度(0.12)、小的静叶出口气流角(13°)、静叶弯曲15°以及加迷宫围带结构等措施。涡轮的空气试验表明,设计点涡轮效率达83%。The characteristics of Staged Combustion Liquid Rocket Engine turbine were big tip clearance, and thus high loss. Several measures were adopted to increase the efficiency such as low reaction （0. 12） , low stator exit degree （ 13°） , stator blade curving 15° and shroud with labyrinth. The air simulation test showed an efficiency of 83% at designed condition.

关 键 词：液体火箭发动机 涡轮 叶顶间隙 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]