航天推进技术研究院主办
[1]王明华,陈劲松.发动机喷管内流场对流换热系数影响因素的数值分析[J].火箭推进,2011,37(03):32-37.
WANG Ming-hua,CHEN Jin-song.Numerical analysis of influence factor on convective heat transfer coefficient about nozzle internal flow[J].Journal of Rocket Propulsion,2011,37(03):32-37.
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WANG Ming-hua,CHEN Jin-song.Numerical analysis of influence factor on convective heat transfer coefficient about nozzle internal flow[J].Journal of Rocket Propulsion,2011,37(03):32-37.
发动机喷管内流场对流换热系数影响因素的数值分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
37
期数:
2011年03期
页码:
32-37
栏目:
研究与设计
出版日期:
2011-06-15
- Title:
- Numerical analysis of influence factor on convective heat transfer coefficient about nozzle internal flow
- 文章编号:
- 1672-9374(2011)03-0032-06
- Keywords:
- convective heat transfer coefficient of rocket nozzle; mesh Reynolds number; constant temperature wall; boundary layer; aerothermodynamics
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 基于Roe-FDS格式，采用标准k-ε湍流模型对某液氧煤油发动机喷管内部燃气流对喷管内壁的对流传热换热系数进行了数值仿真与研究，分析了网格雷诺数以及恒温壁壁温对喷管内壁对流换热系数的影响。当近壁面网格第一层法向高度为10-3 mm数量级时，仿真结果与工程估算公式的计算结果相吻合。同时，在一定范围内，对流换热系数随来流速度的增大而增大，恒温壁的壁温对对流换热系数的影响则较小。
- Abstract:
- The convective heat transfer coefficient of nozzle internal flow in a liquid oxygen-kerosene rocket engine is simulated with Roe-FDS computation format and a standard k-ε turbulence model. The effects of mesh Reynolds number and constant wall temperature on the convective heat transfer of nozzle internal flow are analyzed. The simulated result is in good agreement with the result of engineering estimation when the order of magnitude of first near-wall mesh altitude is 10-3 mm. In a given scope, the convective heat transfer coefficient increases with the increase of flow velocity, and the influence of constant wall temperature on the convective heat transfer coefficient is indistinctive.
参考文献/References:
[1]阎超, 禹建军, 李君哲. 热流CFD计算中格式和网格效应若干问题研究[J]. 空气动力学学报, 2006, 24(1): 127-132.
[2]SWAMINATHAN V, SETTY Speenivasa, RAMAMADHAV B S. A method for the evaluation of temperature in rocket motor nozzles with varying heat transfer coefficients, AIAA 75-1347 [R]. USA: AIAA, 1975.
[3]李君哲, 阎超, 柯伦, 等. 气动热CFD计算的格式效应研究[J]. 北京航空航天大学学报, 2003, 29(11): 76-79.
[4]覃文洁, 胡春光, 郭良平, 等. 近壁面网格尺寸对湍流计算的影响[J]. 北京理工大学学报, 2006, 26(5): 16-20.
[5]杨世铭, 陶文铨. 传热学(第四版)[M]. 高等教育出版社, 2006.
[6]B K 科什金. 航空与火箭技术中的传热原理[M]. 北京: 科学出版社, 1963.
[7]张宏伟, 陶文铨, 何雅玲, 等. 再生冷却推力室耦合传热数值模拟[J]. 航空动力学报, 2006, 21(5): 148-154.
[8]TOMIFUMI Godai, YOSHINORI Yuzawa, KATUYA Ito, et al. An experimental investigation of heat transfer in the nozzle of high-aluminized solid rocket, NASA TT F-12 [R]. [S. l.]: NASA TT, 1968.
备注/Memo
收稿日期：2011-02-10；修回日期：2011-02-06
作者简介： 王明华（1984—），女，硕士研究生，研究领域为发射燃气动力学
更新日期/Last Update:
1900-01-01