弹用涡喷发动机燃烧室出口温度场试验与分析

推进技术 ›› 2001, Vol. 22 ›› Issue (3): 187-190.

弹用涡喷发动机燃烧室出口温度场试验与分析

郑严,沈倍毅

哈尔滨工业大学能源科学与工程学院!黑龙江哈尔滨150001;航天机电集团公司31所!北京100074

发布日期:2021-08-15

Tests and analysis of exit temperature distribution of the combustor for missile turbojet

School of Energy Science and Engineering,Harbin Inst.of Technology,Harbin 150001,China;The 31th Research Inst.,Beijing 100074,China

Published:2021-08-15

摘要/Abstract

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。

关键词: 涡轮喷气发动机;燃烧室;部件试验;温度分布

Abstract: 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.It is useful for the hot design of the turbine nozzle blades.

Key words: Turbojet engine;Combustor;Component test;Temperature distribution

郑严,沈倍毅. 弹用涡喷发动机燃烧室出口温度场试验与分析[J]. 推进技术, 2001, 22(3): 187-190.