航天推进技术研究院主办
[1]吕发正,吴海波,杨永红,等.液氧牒油高压推力室液膜冷却环局部过热分析[J].火箭推进,2009,35(03):11-14.
Lti Fazhen9,Wu Haib0,Yang Yonghon9,et al.Investigation on local overheating of the film cooling ring for LOX／kerosene high pressure chamber[J].Journal of Rocket Propulsion,2009,35(03):11-14.
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Lti Fazhen9,Wu Haib0,Yang Yonghon9,et al.Investigation on local overheating of the film cooling ring for LOX／kerosene high pressure chamber[J].Journal of Rocket Propulsion,2009,35(03):11-14.
液氧牒油高压推力室液膜冷却环局部过热分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
35
期数:
2009年03期
页码:
11-14
栏目:
研究与设计
出版日期:
2009-06-30
- Title:
- Investigation on local overheating of the film cooling ring for LOX／kerosene high pressure chamber
- Keywords:
- liquid rocket engine; thrust chamber; film cooling; heat transfer; ablation
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 液氧／煤油发动机高压推力室采用了多条液膜冷却环带技术。由于室压高和热流 密度大，易出现冷却环带结构局部过热现象，局部过热(甚至局部烧蚀)有时发生在燃烧室 收缩段的冷却环上沿。传热计算和对比分析表明。在降低边区混合比的同时。第一冷却环带 流量增大25％，可使过热处气壁温下降约35℃。采取增加冷却环带流量、降低燃烧室边区混 合比、改善液膜冷却局部喷注结构等措施有利于燃烧室壁面的热防护．可防止局部过热的发 生。
- Abstract:
- The multi-ring film cooling technique was introduced for thermal protection of the high pressure chamber of LOX／kerosene engine．The local overheating(even ablation)of the film cooling structure oceurred ocassionally at the slot step(aft lip)due to the high chamber pressure with large heat flux．The comparison analysis of heat transfer calculation was conducted，and the re— suits show that the hot-gas side wall temperature can reduce about 35 oC by increasing the flow rate by 25％and a lower peripheral mixture ratio．The measures of increasing film cooling flow rate，de— creasing peripheral mixture ratio and improving the local film ring structure aye effective for chamber wall thermal protection and preventing local overheating or ablation．
参考文献/References:
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备注/Memo
收稿日期：2009-03—26；修回日期：2009--04-10。基金项目： “863”高技术项目。 作者简介：吕发正(1968～)，男，高级工程师，研究领域为液体火箭发动机推力室设计。
更新日期/Last Update:
1900-01-01