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为提高比冲，闭环系统的液体火箭发动机的涡轮泵多采用反力度不大的反力式涡轮，这种火箭反力式涡轮不同于航空涡轮，其以极低的压比、极高的负荷和低展弦比为特征，在给定的叶栅大气流转折角、低展弦比、低反力度和相对大的径向间隙条件下，采用了沿叶高正攻角设计和沿叶高变功率损失设计，用以加大叶栅通道的几何收敛性，减少二次流和叶顶间隙损失，从而获得相对高的涡轮效率．
To improve the specific impulse, the liquid rocket engine turbo pump closed-loop system to use less anti-reaction turbine, the rocket anti-turbine is different from the aviation turbine, which at very low pressure ratio, high load And low aspect ratio. With a given cascade flow angle, low aspect ratio, low reverse force and relatively large radial clearance, the design of the positive angle of attack along the blade and the variation of the blade height The power loss design is used to increase the geometrical convergence of the cascade channel and reduce the secondary flow and tip clearance loss so as to obtain relatively high turbine efficiency.