航天推进技术研究院主办
[1]王太平,孙冰,薛立鹏,等.氢氧发动机非均匀圆孔头部气膜冷却数值模拟[J].火箭推进,2022,48(04):1-12.
WANG Taiping,SUN Bing,XUE Lipeng,et al.Numerical simulation of non-uniform circular-hole film cooling at the near-injection region of hydrogen/oxygen rocket engine[J].Journal of Rocket Propulsion,2022,48(04):1-12.
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WANG Taiping,SUN Bing,XUE Lipeng,et al.Numerical simulation of non-uniform circular-hole film cooling at the near-injection region of hydrogen/oxygen rocket engine[J].Journal of Rocket Propulsion,2022,48(04):1-12.
氢氧发动机非均匀圆孔头部气膜冷却数值模拟
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年04期
页码:
1-12
栏目:
目次
出版日期:
2022-08-21
- Title:
- Numerical simulation of non-uniform circular-hole film cooling at the near-injection region of hydrogen/oxygen rocket engine
- 文章编号:
- 1672-9374(2022)04-0001-12
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 氢氧火箭发动机燃烧室壁面热环境十分恶劣,头部气膜冷却是主要辅助冷却手段之一,圆孔头部气膜冷却是重要的设计方案。对圆孔型头部气膜进行了三维数值仿真研究,考虑推力室外部再生冷却的影响,通过全面数值实验分析了气膜流量占比、气膜孔直径和相邻气膜孔面积比等参数的影响,提出一种非均匀分布的圆孔头部气膜冷却方案。结果表明,在氢氧火箭发动机圆孔头部气膜冷却中,存在一个最佳吹风比使得头部区域冷却效果最好,最佳吹风比的值由气膜流量占比和气膜孔直径共同决定,最佳吹风比介于5.454～5.849之间 通过合理的非均匀圆孔气膜结构设计,控制相邻气膜孔面积比在0.6～0.8范围内,采用提出的非均匀气膜孔方案有利于提高燃烧室的整体性能。
- Abstract:
- The thermal environment of the combustion chamber wall in hydrogen/oxygen rocket engine is very harsh, and the circular-hole film cooling is one of the main auxiliary methods to reduce the heat load in the near-injection region.In this study,the three-dimensional numerical simulation of the head gas film with cylindrical film hole was carried out, considering the influence of regenerative cooling outside the thrust chamber.Through comprehensive numerical experiments, the effects of parameters such as the proportion of gas film flow ratio, the diameter of film hole and the area ratio of adjacent film holes, and a gas film cooling scheme of circular hole head with non-uniform distribution was proposed.The results show that there is an optimal blowing ratio to make the cooling effect of the head area the best in the film cooling of the head of the hydrogen/oxygen rocket engine.The optimal blowing ratio is determined by the ratio of the air film flow rate and the diameter of the air film hole, and the optimal air blowing ratio in this study is between 5.454 and 5.849.Through the reasonable structure design of the non-uniform circular-hole, the area ratio of adjacent gas film holes is controlled within the range of 0.6-0.8.The proposed non-uniform film hole scheme is beneficial to the improvement of the overall combustion chamber performance, which can provide a reference for engineering design.
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备注/Memo
收稿日期:2021-01-21 修回日期:2021-02-25
作者简介:王太平(1990—),男,博士,工程师,研究领域为液体火箭发动机热防护、阀门设计。
更新日期/Last Update:
1900-01-01