航天推进技术研究院主办
火箭发动机的正反转涡轮设计
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
期数:
2004年02期
页码:
54-58
栏目:
出版日期:
1900-01-01
- Title:
- Counter-rotating Turbine Designed for Turbopump Rocket Engine
- 分类号:
- V432
- 文献标志码:
- A
- 摘要:
- 一项减少重复成本的主要方法就是限制零件数量和简化机械结构。涡轮泵在火箭发动机总成本中占有很大一部分,大约是30%,因此,理应对涡轮泵进行设计简化。对于可贮存的液氧/烃或者液氧/甲烷火箭发动机,把涡轮泵设计成一轴化是有价值的。然而,对于液氧/液氢发动机,由于两推进剂密度之间存在着巨大的差异,因此,最佳方案就是燃料泵和氧化剂泵分别采用不同的转速驱动。在这种方案中,可以仅用一个涡轮来带动液氧和液氢泵,不过两泵之间要通过齿轮来传递转速,例如HM7或RL10发动机就是这样的结构。但是,齿轮在低温环境中的工作是不可靠
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更新日期/Last Update:
1900-01-01