亚燃冲压燃烧室隔热屏壁温试验研究

Experimental Investigation on Heat Shield Temperature of Ramjet Combustor

亚燃冲压燃烧室在高空、高马赫数下工作时,其进气温度很高,冷却空气量少,给冷却设计带来很大困难。本文通过试验,研究了热障涂层和两种不同燃油喷射方式对某型亚燃冲压燃烧室隔热屏壁温的影响。结果表明:热障涂层对降低隔热屏壁温有一定的作用,喷油孔分布均匀的燃油喷射装置对冲压燃烧室冷却设计更有利。本研究可为亚燃冲压燃烧室的冷却设计提供参考。

It is difficult to design ramjet combustor cooling system for high temperature inlet air and less cooling air at altitude and high Mach number.The impacts of thermal barrier coatings（TBCs） and two types of fuel injection on ramjet combustor heat shield wall temperature were investigated.The experimental results showed that TBCs are useful to reduce heat shield temperature,and the uniformity of fuel injector distribution is more favorable for ramjet combustor cooling system design.It gives reference to the design of ramjet combustor cooling system.