基于高温热管的超燃燃烧室热防护结构

韩海涛; 陈智; 胡龙飞; 陈思员; 艾邦成; 俞继军; 曲伟

doi:10.13224/j.cnki.jasp.2017.05.003

基于高温热管的超燃燃烧室热防护结构

doi: 10.13224/j.cnki.jasp.2017.05.003

中国航天科技集团公司中国航天空气动力技术研究院，北京 100074

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出版历程
- 收稿日期: 2015-08-23
- 刊出日期: 2017-05-28

High temperature heat pipe enhanced thermal protection structure for scramjet combustion chamber

摘要

摘要: 提出了基于先进热管理思想的燃烧室热防护结构.面板采用腔体式平板高温热管，实现面板等温化，降低局部高温区的温度；在热管腔体内部设计燃油冷却通道，实现对超燃燃烧室面板的燃油主动冷却.对其各项性能进行了数值分析，给出了设计参数对系统性能的影响规律，并完成了结构样件研制及石英灯试验考核.典型设计状态下，其单位面积质量为无氧铜面板的35.4%，高温合金面板的38.2%.石英灯局部加热条件下，面板最高温度为1123K时最大温差为80K.相比于传统燃油冷却方式，该型防热结构能够有效提高超燃发动机燃烧室热防护的整体性能，是超燃发动机热防护的一种重要概念.
- 热管 /
- 超燃 /
- 燃烧室 /
- 热防护 /
- 燃油管
Abstract: Based on advanced thermal management method, a novel thermal protection structure was proposed for scramjet combustion chamber. High temperature heat pipe panels were used to decrease the local high temperature by achieving isotherm. Simultaneously, fuel pipes were embedded to achieve active cooling. The performance was analyzed by numerical simulation, and the influences of the design parameters were evaluated. A sample panel was prepared and evaluated by quartz lamp heating test. In typical circumstance, its unit area mass was 35.4% and 38.2% of oxygen-free copper panel and high temperature super alloy panel, respectively. The maximum temperature difference was less than 80K when the maximum temperature was 1123K in the local heating test. As a proposed thermal protection method, the structure can improve the scramjet thermal protection performance compared with the traditional fuel cooling method.
- heat pipe /
- scramjet /
- combustion chamber /
- thermal protection /
- fuel pipe

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参考文献(16)

[1]	Uhrig G,Bouquet C,Larrieu J M,et al.Composite technologies development status for scramjet applications［R］.Norfolk,Virginia:12th AIAA Space Planes and Hypersonic Systems and Technologies Conference,2003.
[2]	Wishart D P,Fortin T B,Guinan D,et al.Design,fabrication and testing of an actively cooled scramjet propulsion system［R］.AIAA-2003-0015,2003.
[3]	Zander F,Morgan R.Composite scramjet combustor［R］.AIAA-2009-7354,2009.
[4]	范学军,俞刚.大庆 RP-3 航空煤油热物性分析［J］.推进技术,2006,27(2):187-192. FAN Xuejun,YU Gang.Analysis of thermophysical properties of Daqing RP-3 aviation kerosene［J］.Journal of Propulsion Technology,2006,27(2):187-192.(in Chinese)
[5]	Zhong F,Fan X,Yu G,et al.Heat transfer of aviation kerosene at supercritical conditions［J］.Journal of Thermophysics and Heat Transfer,2009,23(3):543-550.
[6]	张春本,邓宏武,徐国强,等.超临界压力下航空煤油 RP-3 焓值的测量及换热研究［J］.航空动力学报,2010,25 (2): 331-335. ZHANG Chunben,DENG Hongwu,XU Guoqiang,et al.Enthalpy measurement and heat transfer investigation of RP-3 kerosene at super critical pressure［J］.Journal of Aerospace Power,2010,25(2):331-335.(in Chinese)
[7]	蒋劲,张若凌,乐嘉陵.超燃冲压发动机再生冷却热结构设计的计算工具［J］.实验流体力学,2006,20(3):1-7. JIANG Jin,ZHANG Ruoling,LE Jialing.The calculational tool of thermal structure design for regeneratively cooled scramjet［J］.Journal of Experiments in Fluid Mechanics,2006,20(3):1-7.(in Chinese)
[8]	夏新林,艾青.一种再生冷却面板的温度控制热设计方法［J］.航空动力学报,2010,25(1):1-5. XIA Xinlin,AI Qing.Thermal design method of temperature control for regenerative cooling panel［J］.Journal of Aerospace Power,2010,25(1):1-5.(in Chinese)
[9]	蒋劲,张若凌,乐嘉陵.再生冷却超燃冲压发动机整机稳态热分析［J］.航空动力学报,2009,24(12):2649-2654. JIANG Jin,ZHANG Ruoling,LE Jialing.Steady thermal analysis of regeneratively cooled scramjet［J］.Journal of Aerospace Power,2009,24(12):2649-2654.(in Chinese)
[10]	鲍文,周伟星,周有新,等.超燃冲压发动机再生冷却结构的强化换热优化研究［J］.宇航学报,2008,29(1):246-251,310. BAO Wen,ZHOU Weixing,ZHOU Youxin,et al.Active cooling design on heat transfer enhancement for scramjet engines using optimization methods［J］.Journal of Astronautics,2008,29(1):246-251,310.(in Chinese)
[11]	蒋劲,张若凌,杨样,等.超燃冲压发动机典型部件热防护［J］.航空动力学报,2013,28(9):1921-1926. JIANG Jin,ZHANG Ruoling,YANG Yang,et al.Thermal protection of scramjet typical components［J］.Journal of Aerospace Power,2013,28 (9):1921-1926.(in Chinese)
[12]	姜贵庆,艾邦成,俞继军.疏导热防护的固体传导的性能表征与传导特性分析［J］.空气动力学学报,2008,26(1):44-50. JIANG Guiqing,AI Bangcheng,YU Jijun.The property expression and conduction analysis of solid medium for Shu-Dao thermal protection［J］.Acta Aerodynamica Sinica,2008,26(1):44-50.(in Chinese)
[13]	李锋,艾邦成,姜贵庆,等.高超声速飞行器疏导式热防护研究进展［J］.气体物理-理论与应用,2010,5(2):95-104.LI Feng,AI Bangcheng,JIANG Guiqing,et al.Advances in research of hypersonic vehicle leading thermal protection［J］.Physics of Gases-Theory and Applications,2010,5(2):95-104.(in Chinese)
[14]	韩海涛,邓代英,陈思员,等.尖前缘一体化高温热管结构设计与分析［J］.机械强度,2013,35(1):48-52.HAN Haitao,DENG Daiying,CHEN Siyuan,et al.Design and structural analysis of sharp leading edge integrated with heat pipe［J］.Journal of Mechanical Strength,2013,35(1):48-52.(in Chinese)
[15]	赵蔚琳,刘宗明,李树人.高温热管的研究与发展［J］.石油化工设备,2005,34(4):40-44.ZHAO Weilin,LIU Zongming,LI Shuren.Research and development of the high temperature heat pipe［J］.Petro-Chemical Equipment,2005,34(4):40-44.(in Chinese)
[16]	黄生云,郭航,叶芳.热管启动性能研究进展［J］.现代化工,2009(7):27-30.HUANG Shengyun,GUO Hang,YE Fang.Advances in study of start-up performance of heat pipes［J］.Modern Chemical Industry,2009(7):27-30.(in Chinese)