燃烧室主燃孔下游气膜绝热温比研究  

Adiabatic film cooling effectiveness downstream of primary jet in combustion chamber

作　　者：林宇震[1] 袁怡祥[1] 刘高恩[1] 谢川华 

机构地区：[1]北京航空航天大学热动力工程研究所,北京100083

出　　处：《推进技术》2002年第4期273-275,331,共4页Journal of Propulsion Technology

摘　　要：对单个主燃孔射流下游的缝槽气膜绝热温比进行的实验研究中 ,采用了CO2 传热传质类比方法测量气膜的绝热温比 ,考虑了三种气膜吹风比和两种主燃孔射流动量比。研究结果表明 :主燃孔射流的引入破坏了气膜的完整性 ,相对于正常气膜的绝热温比值 ,主燃孔射流正下游区域的气膜绝热温比大幅度下降 ,在横向偏离主燃孔射流较远的下游区域 ,气膜绝热温比有一定程度的下降 ;气膜吹风比对气膜绝热温比的下降有较大影响 。The experimental investigations were taken on the slot film cooling adiabatic effectiveness downstream the primary jet using heat mass transfer analogy method with the sample gas CO 2 Three film blowing ratios and two primary jet momentum ratios were taken into consideration in the experiment Results show that the adiabatic wall film cooling effectiveness right downstream the primary jet was much lower than normal film due to the integrity of film disrupted by jet, and the adiabatic wall film cooling effectiveness is less lower in the region beside the right downstream the primary jet Film blowing ratios marked influence on the decrease of the adiabatic film cooling effectiveness, on the contrary the jet momentum ratios had little influence on the decrease of the adiabatic film cooling effectiveness

关 键 词：气膜 绝热温比 航空发动机 燃烧室 薄膜冷却 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]