Abstract: According to the characteristics of astronautical reaction turbine used in high performance liquid rocket engine with staged combustion in closed circulation, the designed rotor cascade and blade to blade flow in the cascade were investigated. For existed rotor cascade, the effects of positive or negative attacking angle of the reaction turbine on the energy loss and blade to blade flow also were studied by means of two dimensional cascade experiments in the subsonic tunnel. The results indicate: in order to obtain the continuous contraction of the geometrical cascade and less energy loss the positive attacking angle was adopted for rotor design. For the existed contracting rotor cascade, the negative attacking angle condition results in the less energy loss.

Key words: High pressure staged combustion rocket engine;Reaction expansion turbine;High loading turbine;Turbin rotor;Attacking angle

摘要： 针对高性能分级燃烧(闭式)循环液体火箭发动机用反力式涡轮的特点,对所设计的动叶叶栅S1流面的准三元流气动分析和已有动叶平面叶栅的亚声速风洞试验,研究了反力式涡轮动叶正负攻角对叶栅内的绕流和能量损失的影响。结果表明:对于给定的来流方向,为得到连续收敛的叶栅几何通道和小的能量损失,动叶应采用正攻角设计。对已有的连续收敛的动叶叶栅,应采用负攻角流入工况,能量损失小。

关键词: 高压补燃火箭发动机;反力式涡轮;高载荷涡轮;涡轮转子;进口攻角