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.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2009年第2期695-698,共4页
Journal of Astronautics
