进气径向畸变对燃烧室性能影响研究与预测  

Research and Prediction of the Impact of Inlet Radial Distortion on Combustion Chamber Performance

作　　者：张轲 石云姣 姚建朋 罗绍文 赵宁波[2] 杨仁[2] ZHANG Ke;SHI Yun-jiao;YAO Jian-peng;LUO Shao-wen;ZHAO Ning-bo;YANG Ren(AECC Shenyang Engine Research Institute,Shengyang 110015,China;College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]哈尔滨工程大学动力与能源工程学院,哈尔滨150001

出　　处：《航空发动机》2023年第5期40-46,共7页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：针对燃气轮机在实际运行过程中燃烧室进口速度分布不均匀问题,采用数值模拟方法对直流环形燃烧室开展数值模拟计算,分析了不同进气速度畸变位置与畸变强度下燃烧室的流场与温度分布特性,并给出了一种畸变条件下燃烧室性能预测模型。结果表明:不同进气速度径向畸变位置与畸变强度对扩压器内和机匣前段流场形态影响较大,燃烧室空气分配比例改变,温度分布有所差异。燃烧室工况改变对空气分配比例、燃烧效率和总压损失的影响不大。进气速度畸变对燃烧效率影响不大,主要影响到总压损失的变化。随着畸变程度提高,空气分配比例变化明显,总压损失随之增大。进气畸变对燃烧室出口温度分布的影响规律较为复杂,影响程度与进气畸变的不均匀度、畸变形式和工况密切相关,变化范围为-30%~20%。在此基础上,给出了适用于进气径向畸变条件下的燃烧室部件特性预测模型,经验证预测模型的误差在3.5%以下。To solve the problem of non-uniform velocity distribution at the inlet of the combustion chamber during the actual operation of a gas turbine,the numerical simulations were carried out for a straight-through annular combustion chamber.The flow field and temperature distribution characteristics of the combustion chamber under different inlet velocity distortion positions and intensities were analyzed,and a performance prediction model of the combustion chamber under distortion conditions was proposed.The results show that the positions and intensities of radial distortion at different inlet velocities have a significant impact on the flow field in diffuser and in front of casing.The air distribution ratio of the combustion chamber changes and the temperature distribution varies.The impact of changes in combustion chamber conditions on air distribution ratio,combustion efficiency,and total pressure loss is not significant.The inlet velocity distortion has little effect on combustion efficiency,mainly affecting the variation of total pressure loss.As the degree of distortion increases,the air distribution ratio changes more significantly,and the total pressure loss increases accordingly.The influence of inlet distortion on the temperature distribution of combustion chamber outlet is relatively complex,and the degree of influence is closely related to the degree of distortion,distortion form,and working conditions,with a variation range of-30%~20%.On this basis,a combustion chamber component characteristic prediction model suitable for radial inlet distortion conditions was proposed,and the error of the prediction model was verified to be within 3.5%.

关 键 词：进气速度畸变 燃气轮机燃烧室 性能预测 燃烧效率 总压损失 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]