某型燃气轮机燃烧室出口温度场的调试  

Experiment on outlet temperature field of a gas turbine combustor

作　　者：刘凯[1] 张宝诚[1] 马洪安[1] 

机构地区：[1]沈阳航空航天大学航空航天工程学部,沈阳110136

出　　处：《航空动力学报》2013年第6期1387-1391,共5页Journal of Aerospace Power

基　　金：国家高技术研究发展计划(2002AA503010)

摘　　要：试验研究了某型燃气轮机燃烧室掺混孔孔径比、相对孔距对出口温度场的影响.试验结果表明:随孔径比的增加,出口温度分布系数逐渐减小,但过大的孔径比易形成局部阻塞,使热点温度升高;孔径比对径向温度分布系数影响较小,仅使温度分布曲线位置移动而不会改变其形状.相对孔距与径向温度分布系数相关性较强,过大(大于0.33)、过小(小于0.29)均不利于掺混.该研究情况下,相对孔距为0.31、孔径比为0.32左右基本合理.The influence of aperture ratio and center distance of a gas turbine combustor mixing system on outlet temperature field was studied experimentally.Experimental results indicate：the outlet temperature distribution coefficient reduces gradually with the increase of aperture ratio.But too large aperture ratio will lead to partial obstruction and also hot spot temperature rise;aperture ratio does not change the radial temperature distribution curve shape,but only bring about shift of its position.Relative center distance and the radial temperature distribution coefficient have a strong correlation,too large（more than 0.33） or too small（less than 0.29） is not helpful for dilution.Relative center distance of 0.31 and aperture ratio of 0.32 are basically reasonable in this case.

关 键 词：燃气轮机 燃烧室 掺混孔 出口温度场 射流 

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] TK474[动力工程及工程热物理—动力机械及工程]