某型发动机涡轮前后温度分布的研究  

AN INVESTIGATION OF TEMPERATURE PROFILE BEFORE AND AFTER TURBINE IN A TYPE OF ENGINE

作　　者：张洪滨[1] 李光中[1] 

机构地区：[1]空军第一研究所,北京100076

出　　处：《推进技术》1997年第5期69-72,共4页Journal of Propulsion Technology

摘　　要：阐述了在某型涡喷发动机上测量涡轮前、后温度分布的方法，并对测量结果进行了分析，得出"涡轮后温度分布不能代替燃烧室出口（涡轮前）温度分布"的结论。The temperature profile quality at engine combustor exit (before turbine) is aimportant technical index, which concern operational reliability and life of engine's thermalcomponent, thus measuring temperature profile at the combustor exit (before turbine) in a engine isvery important. The method of measuring temperature profile before and after turbine in a typeturbojet is presented and the measured results is analysed. It can be concluded that the aftertemperature profile turbine differs from the one before turbine.

关 键 词：燃烧室 涡轮 进口总温 排气总温 温度分布 航空 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]