摘要
介绍了弹用涡喷发动机燃烧室部件试验 ,对试验结果进行了全面的分析 ,指出燃烧室模拟试验与发动机实际工况之间的差别 ,产生差别的原因以及试验修正的方法。通过试验数据的分析与处理给出了某弹用涡喷发动机燃烧室出口径向温度分布、出口温度场和无因次温度场。分析结论可以用于弹用涡喷发动机燃烧室出口温度场预测和涡轮导向器叶片热设计。
The overall tests of exit temperature distribution of the combustor used in missile's turbine jet engine were presented and the statistic analysis results for the tests were given. The differences between imitate tests of the combustor and reality working process of the engine were pointed out. The reasons causing the differences and modifying technique are given. In addition, the temperature distribute on radial and on exit field of combustor were presented. The conclusion is useful for the hot design of the turbine nozzle blades.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2001年第3期187-190,206,共5页
Journal of Propulsion Technology
