火箭发动机喷管辐射及壁温的计算研究

张小英; 蔡国飙; 朱定强

火箭发动机喷管辐射及壁温的计算研究

1.
华南理工大学电力学院广州 510640
2.
北京航空航天大学宇航学院, 北京 100083

基金项目: 国防“十五”预研课题(113020402)

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- 被引次数: 0
出版历程
- 收稿日期: 2006-12-06
- 修回日期: 2007-03-07
- 刊出日期: 2008-01-28

Numerical calculation of the radiative heat transfer and wall temperature of the rocket nozzle

1.
School of Electric Power, South China University of Technology, Guangzhou 510640, China
2.
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 研究了火箭发动机复合喷管的耦合换热及瞬态壁温的计算方法,考虑了扩散控制的C/C喉衬的稳态烧蚀,建立了封闭腔-净辐射模型计算喷管内的辐射换热,改进了喷管辐射换热的计算方法.计算了两种复合喷管的壁温随时间的变化,并与有关文献的结果进行对比.研究表明:在火箭发动机喷管的入口段,高温燃气对壁面的辐射换热热流比对流换热热流强;采用封闭腔-净辐射法计算火箭发动机喷管的辐射精度较高.
- 航空、航天推进系统 /
- 火箭发动机 /
- 复合喷管 /
- 辐射换热 /
- 壁温
Abstract: The computation methods for the coupled heat transfer and transient wall temperature of composite walled rocket nozzle were studied.While the stable ablative calculation for C/Cthroat insert was considered,the Enclosure-Radiative Heat Flux model was established to compute the radiative heat transfer in the nozzle,thus improving the calculation method of radiative heat transfer.The time-dependent variations of wall temperature for two composite walled nozzles were computed,and also compared with the results in the literature.The research shows that,the radiative heat transfer is stronger than the convective heat transfer in the entrance section of the nozzle;the Enclosure-Radiative Heat Flux model could compute more precisely the radiative heat transfer of the rocket nozzle.
- aerospace propulsion system /
- rocket engines /
- composite nozzle /
- radiative heat transfer /
- wall temperature

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参考文献(17)

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