航天推进技术研究院主办
[1]高翔宇,孙纪国.推力室多孔面板发汗冷却试验研究[J].火箭推进,2011,37(05):9-12.
GAO Xiang-yu,SUN Ji-guo.Experimental study on porous plate transpiration cooling of thrust chamber[J].Journal of Rocket Propulsion,2011,37(05):9-12.
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GAO Xiang-yu,SUN Ji-guo.Experimental study on porous plate transpiration cooling of thrust chamber[J].Journal of Rocket Propulsion,2011,37(05):9-12.
推力室多孔面板发汗冷却试验研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
37
期数:
2011年05期
页码:
9-12
栏目:
研究与设计
出版日期:
2011-10-15
- Title:
- Experimental study on porous plate transpiration cooling of thrust chamber
- 文章编号:
- 1672-9374(2011)05-0009-04
- Keywords:
- transpiration cooling; porous plate; liquid rocket engine; thrust
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 为了研究液体火箭发动机推力室喷注器多孔面板发汗冷却特性，以缩比推力室挤压热试验的形式开展了多孔面板发汗冷却特性研究，试验采用常温气氢对喷注器多孔面板进行发汗冷却。发汗冷却试验共进行5次，燃烧室压力为3.9～7.6 MPa，燃烧室氢氧混合比为2.8～7.2。研究结果表明在本试验研究状态下面板燃气侧温度为680～830 K，总结了推力室多孔面板渗透率与压降的工程关系式。
- Abstract:
- Hot fire tests were performed on subscale thrust chamber to investigate the transpiration cooling characteristics of thrust chamber injector porous face plate cooled by H2 of room tempe- rature. Five times tests were conducted under the conditions: combustion chamber pressure of 3.9-7.6 MPa, and O/F mixture ratio of 2.8-7.2. The investigation demonstrates that the hot gas wall temperature of the porous plate is 680-830 K under the test conditions. The engineering flow resistance function applied to thrust chamber porous face plate was obtained.
参考文献/References:
[1]丁水汀, 崔亮. 内部冲击和外部气膜的组合特性研究[J]. 航空动力学报, 2007, 22 (2): 25－30.
[2]张峰, 刘伟强. 层板发汗冷却在液体火箭发动机中的应用与发展综述[J]. 火箭推进, 2007, 33 (6): 47－52.
[3]张纯良, 张振鹏. 发汗冷却喷管在火箭发动机上的应用[J]. 上海航天, 2002 (2): 10-14.
[4]BUCCHI A, A CONGIUNTI L, BRUNO C. Investigation of transpiration cooling performance in LOX/Methane liquid rocket engines, IAC-03-S.3.08 [R]. Italy: University of Rome "La Sabienza", 2003.
[5]黄春桃, 孙冰. 层板发汗冷却推力室传热分析[J]. 火箭推进, 2011, 37 (1): 19－23, 41.
[6]SIZEN M, DAVIS P A. Transpiration cooling of a liquid rocket thrust chamber wall, AIAA 2008-4559[R]. USA: AIAA, 2008.
[7]孙纪国, 王建华. 烧结多孔结构的渗透和流阻特性研究[J]. 航空动力学报, 2008, 23(1): 130-133.
[8]ERGUN S. Fluid flow through packed columns[J]. Chem. Eng. Prog., 1952, 48(2): 89-94.
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HUANG Chun-tao,SUN Bing.Heat transfer analysis of platelet transpiration cooling thrust chamber[J].Journal of Rocket Propulsion,2011,37(05):17.
[2]张峰,刘伟强.层板发汗冷却在液体火箭发动机中的应用与发展综述[J].火箭推进,2007,33(06):43.
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[3]高翔宇,孙纪国,田 原.推力室多孔面板氢发汗冷却传热分析[J].火箭推进,2012,38(05):13.
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备注/Memo
收稿日期：2011-06-09；修回日期：2011-08-01
基金项目：国家航天高技术项目
作者简介：高翔宇（1980—），男，硕士，工程师，研究领域为液体火箭发动机燃烧装置设计
更新日期/Last Update:
1900-01-01