航天推进技术研究院主办
[1]刘占一,胡锦华,张魏静,等.多孔介质冷却通道在燃烧室中的应用[J].火箭推进,2020,46(04):54-59.
LIU Zhanyi,HU Jinhua,ZHANG Weijing,et al.Application on combustion chamber of porous medium cooling channel[J].Journal of Rocket Propulsion,2020,46(04):54-59.
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LIU Zhanyi,HU Jinhua,ZHANG Weijing,et al.Application on combustion chamber of porous medium cooling channel[J].Journal of Rocket Propulsion,2020,46(04):54-59.
多孔介质冷却通道在燃烧室中的应用
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
46
期数:
2020年04期
页码:
54-59
栏目:
研究与设计
出版日期:
2020-08-18
- Title:
- Application on combustion chamber of porous medium cooling channel
- 文章编号:
- 1672-9374(2020)04-0054-06
- 分类号:
- V434.3
- 文献标志码:
- A
- 摘要:
- 为了探索多孔介质冷却通道在液体火箭发动机燃烧室中的应用,采用金属粉末烧结法制备了多孔介质,设计了多孔介质通道的流阻和传热特性测试装置,建立了采用多孔介质冷却通道的燃烧室传热预测模型,对具有不同结构参数的多孔介质进行了研究。结果表明:随着孔隙率的增大,多孔介质通道的流阻逐渐减小,换热能力逐渐下降; 基于传热模型的预测结果与试验有一定偏差,最大达到25%; 相较铣槽通道,多孔介质冷却通道能够在燃烧室中获得更好的热防护效果。
- Abstract:
- To investigate the adaptability of porous medium cooling channel in liquid rocket engine combustor,porous medium was manufactured by the method of metal powder sintering. Test devices about flow resistance and heat transfer characteristics of porous medium channel were designed and built,meanwhile,heat transfer prediction model of combustion chamber adopted porous medium channel was established and porous medium channels with different structural parameters were involved in this paper. Results from the research are as follows. The flow resistance and heat transfer intensity of porous medium channel decrease as the void fraction of porous medium increases. The prediction based on heat transfer model has some deviations with the experimental results. The maximum deviation is about 25%. Compared with milled channel,better thermal protection effect could be obtained with porous medium cooling channel in combustion chamber.
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备注/Memo
收稿日期:2019-10-13; 修回日期:2019-11-15
基金项目:液体火箭发动机技术重点实验室基金(6142704180206)
作者简介:刘占一(1985—),男,博士,高级工程师,研究领域为液体火箭发动机技术
更新日期/Last Update:
2020-07-30