超燃冲压发动机典型部件热防护

Thermal protection of scramjet typical components

通过在电弧加热器上的试验考核,对进气道唇口前缘、注油支杆等发动机典型被动热防护部件的材料选择和热结构设计进行了研究.发展了主动冷却燃烧室热结构计算评估方法,将经过试验验证的热分析程序应用于燃烧室主动冷却结构的材料配置研究.材料C1和C2的进气道唇口前缘经过60s试验后情况良好;材料Z1的注油支杆经历50s试验后情况良好;将主动冷却燃烧室热分析计算程序应用于冷却面板试验,温度测量值与计算值最大相差55K,表明计算与试验符合较好,计算程序可为主动冷却燃烧室结构材料配置的设计研究提供可信的参考数据.研究所获得的经验和技术可应用于全流道超燃冲压发动机的设计与验证.

The material selections and thermal-structural designs for the typical passive thermal protection components,such as the cowl leading edges and fuel injection struts,were investigated by the tests on the electric arc heater instrument.The method of thermalstructural analysis for the actively cooled combustor was developed,and the thermal evaluation code validated by the experiments was applied to the combustor material coupon.The cowl leading edges made of materials C1and C2were in good condition after 60stest.The fuel injection struts made of material Z1were in good condition after 50stest.The actively cooled combustor thermal analysis and calculation procedures were applied to the cooling panel tests.The maximum temperature difference between the measurement value and the calculated value was 55K,showing good agreement of the calculation and experiment.So,the calculation program can provide credible reference data for the material configuration design of the actively cooled combustor.The experience and technology learned from the approach will be incorporated into the design and demonstration of complete free jet engine.