燃气轮机过渡段双腔室模型设计及优化  

Design and optimization of double chamber model of gas turbine transition piece

作　　者：刘光洁[1,2] 徐涛[1] 李俊楼[1] 于征磊[3] 修航[1] 程飞[1] 

机构地区：[1]吉林大学机械科学与工程学院,长春130022 [2]长春师范大学计算机科学与技术学院,长春130032 [3]吉林大学生物与农业工程学院,长春130022

出　　处：《吉林大学学报（工学版）》2014年第5期1360-1365,共6页Journal of Jilin University:Engineering and Technology Edition

基　　金：国家自然科学基金项目(50975121);吉林省科技发展计划项目(20126001);长春市科技支撑计划项目(10KZ03)

摘　　要：以燃气轮机燃烧室过渡段结构及性能为研究对象,设计了具有三排冲击孔的过渡段简化双腔室模型。采用正交试验设计、响应面近似建模方法分析求解流场及温度场,得到了双腔室模型内壁面加权平均温度及最小压强关于冲击孔角度、风向倾角的响应面模型。最后,采用内点优化算法对响应面模型进行了优化,得到了最优冲击孔角度及风向倾角,研究了最优及初始冲击孔角度、风向倾角对双腔室模型内壁面冷却性能的影响。结果表明:优化方案冷却效率比初始方案提高了7.53%。仿真分析结果对双腔室结构冲击孔角度设计具有很好的参考价值。The structure and performance of the transition piece of gas combustor were taken as the research objects, and a simplified double chamber model was designed with the distribution of holes in three rows. The response surface model was established by adopting Orthogonal Design of Experiment （（）DOE） and approximate modeling method. The flow field and temperature field were solved using this response surface model. The polynomial regression equations were built about the weighted average temperature and the minimum pressure on the inner-wall of the double chamber model regarding the impinging hole angle and the injection orientation. The optimum impinging hole angle and the injection orientation were found using the interior point method to solve the response surface model. The simulation results show that the cooling efficiency the optimum design proposal was 7.53% higher than that of the initial design proposal. The simulation results and the comparative analysis may provide valuable reference for the impinging hole angle design in double chamber model.

关 键 词：流体力学 燃气轮机 燃烧室结构 冲击孔角度 风向倾角 

分 类 号：O302[理学—力学]