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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 ,而主燃孔射流对气膜绝热温比下降影响小
In the experimental study on the adiabatic temperature ratio of gas film in a slot downstream of a single main-hole jet, CO2 heat and mass transfer analogy was used to measure the adiabatic temperature ratio of the gas film. Three gas-blow ratio and two main Pore jet momentum ratio. The results show that the introduction of the main gushing jet destroys the integrity of the gas film. Compared with the adiabatic temperature ratio of the normal gas film, the temperature adiabatic ratio of the gas film directly downstream of the main gust jet decreases sharply, In the downstream region where the jet flow is far away, the temperature ratio of the gas-film adiabatic declines to a certain degree. The blow-by ratio of the gas film has a greater influence on the decrease of the temperature-adiabatic temperature ratio of the gas film, while the impact of the main gas-