基于高温热管的超燃燃烧室热防护结构  

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

作　　者：韩海涛[1] 陈智[1] 胡龙飞[1] 陈思员[1] 艾邦成[1] 俞继军[1] 曲伟[1] 

机构地区：[1]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

出　　处：《航空动力学报》2017年第5期1043-1050,共8页Journal of Aerospace Power

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1 123K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.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 1 123 K 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.

关 键 词：热管 超燃 燃烧室 热防护 燃油管 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]