斜切径向旋流燃烧室主燃区光学测量与特性分析  

Optical measurement and characteristic analysis of aeroengine combustor primary zone with counter-rotating swirler

作　　者：陈敏[1] 宋文艳[1] 肖隐利[1] 陈亮[1] 李建平[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2013年第8期1727-1735,共9页Journal of Aerospace Power

基　　金：西北工业大学基础研究基金(JC20100213)

摘　　要：针对斜切径向旋流环形燃烧室模型,采用可调谐二极管激光吸收光谱(TDLAS)、相干反斯托克斯喇曼光谱(CARS)光学测量手段,在模化状态(Case 2)下,对燃烧室主燃区进行温度测量,分别得到了主燃区内12个点的温度和沿两条路径的积分温度.使用Fluent 12.0对Case 2进行数值模拟,分别使用两种非预混燃烧模型:平衡化学反应模型(EM)和稳态层流小火焰(SLF)模型.通过将两种不同燃烧模型的计算结果与TDLAS,CARS试验测量数据作对比验证,发现EM计算得到的温度更高,并与试验测量温度更符合,其中与CARS测量的误差小于6%.在试验验证的基础上,完成燃烧室在冷流状态(Case 1)下的计算,分析主燃区的气流组织和主燃孔射流对回流区的影响;利用EM计算分析燃烧室主燃区在全压状态(Case 3)下燃料分布、温度场、组分分布和性能参数,如燃烧室的燃烧效率为0.97、出口温度分布系数为0.312等,较为全面反映了燃烧室内气流流动换热和燃烧现象.For an aeroengine annular combustor model,coherent anti-Stokes Raman scattering（CARS） and tunable diode laser absorption spectroscopy（TDLAS） were used to measure temperature in primary zone（PZ） for modeling condition（Case 2）.Based on Fluent 12.0 software,two different non-premixed combustion models equilibrium model（EM） and steady laminar flamelet（SLF） model were adopted to calculate the combustor performances for the same case.Then comparison between spectral measured temperature and numerical simulated one shows that higher and more accurate prediction were achieved by EM.What＇s more,the errors between EM calculation and CARS measurement are less than 6%.For cold flow condition（Case 1）,not only detailed analysis of flow field in PZ was made,but also the influence of primary jet on recirculation zone was investigated.Because of the advantage EM was used for full pressure condition（Case 3） to analyze reaction flow field in PZ and calculate combustor performances,including combustion efficiency（0.97）,overall temperature distribution factor（OTDF）（0.312）,etc.These results indicate reasonable heat transfer and combustion phenomena in combustor model.

关 键 词：可调谐二极管激光吸收光谱(TDLAS) 相干反斯托克斯喇曼光谱(CARS) 平衡化学反应模型 稳态层流小火焰面模型 主燃区 

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]