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

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