航天推进技术研究院主办
[1]李应强.液体火箭发动机涡轮火药燃气
供应系统性能研究[J].火箭推进,2008,34(06):14-18.
Li Yingqiang.Performance research on turbine powder gas fleed system in liquid rocket engine[J].Journal of Rocket Propulsion,2008,34(06):14-18.
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Li Yingqiang.Performance research on turbine powder gas fleed system in liquid rocket engine[J].Journal of Rocket Propulsion,2008,34(06):14-18.
液体火箭发动机涡轮火药燃气 供应系统性能研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
34
期数:
2008年06期
页码:
14-18
栏目:
研究与设计
出版日期:
2008-12-30
- Title:
- Performance research on turbine powder gas fleed system in liquid rocket engine
- Keywords:
- liquid rocket engine; turbine nozzle; powder gas
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 采用变燃面装药固体火箭发动机的“瞬时压强平衡法”和流量平衡的关系式。 较准确地对涡轮喷嘴前火药燃气性能进行了计算，得到了涡轮喷嘴前火药燃气性能的各种参 数，这些参数有助于对涡轮起动性能和发动机加速性的研究。
- Abstract:
- This article adopts the method of instantaneous pressure equilibrium of variational buming sud．ace of powder in solid mcket engine and now—rate equilibrium relation to calculate ex． actly the performance of powder gas in the front of the turbine nozzle．Various performance parame— ters of the powder gas in the front of the turbine nozzle were obtained．These parameters will be helpful to the research of turbine start and engine acceleration perfoHnances．
参考文献/References:
[1]李宜敏，张中钦，赵元修．固体火箭发动机原理[M]．北
京：国防工业出版社，1985．
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京：国防工业出版社．2005．
[41王光林，蔡娥．固体火箭发动机设计[M]．航空工业教材
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[J]．火箭推进，2007，33(4)：16—20．
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(1)：8—14．
[8]刘巍，杨涛，胡建新，等，气氧／酒精火炬式点火器试验
[J]．推进技术，2008，29(3)：269—273．
[9]郭K K，萨默菲尔德M．固体推进剂燃烧基础(下)[M]．
朱贵荣，于广经，廉茂林，等译。北京：宇航出版社，
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备注/Memo
收稿日期：2008—06—17；修回日期：2008一08—26。 作者简介：李应强(1968一)，男，高级工程师，研究领域为同体动力装置及火工品技术。
更新日期/Last Update:
1900-01-01