北京航空航天大学学报 ›› 1999, Vol. 25 ›› Issue (6): 696-699.

• 论文 • 上一篇    下一篇

液体火箭发动机高效率反力式涡轮的设计

庄毓南1, 张国舟1, 刘中祥2, 魏沫2   

  1. 1. 北京航空航天大学 宇航学院;
    2. 北京丰源机械研究所
  • 收稿日期:1999-04-30 出版日期:1999-06-30 发布日期:2010-09-28
  • 作者简介:女 61岁 教授 100083 北京

Design of Rocket Reaction Turbine for High Efficiency

Zhuang Yunan1, Zhang Guozhou1, Liu Zhongxiang2, Wei Mo2   

  1. 1. Beijing University of Aeronautics and Astronautics,School of Astronautics;
    2. Beijing Fengyuan Machinery Institute
  • Received:1999-04-30 Online:1999-06-30 Published:2010-09-28

摘要: 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.

Abstract: In order to gain higher specific impulse, the rocket turbines for the closed cycle are reaction turbines with a lower reaction in the rotating vanes. This rocket reaction turbine is characterized by lowest pressure ratio,highest load and low aspect ratio. Under the design conditions of large medium flow deflective angle in the turbine cascade, low aspect ratio and large relative rotor tip clearance, the positive attack angle design along the height of the vanes,varying load and varying loss design along the height of the vanes are adopted in order to minimize the secondary loss,the tip clearance loss and gain the high efficiency for the rocket reaction turbine.

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