涡轮转子内动态燃烧模型机理探讨  

Discussion on the mechanism of dynamic combustion model in turbine rotor

作　　者：郑海飞[1] 唐豪[2] TANG Hao;ZHENG Haifei(Shanghai Aircraft Design and Research Institute,Center of Airworthiness Engineering Shanghai 201210,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]上海飞机设计研究院适航工程中心,上海201210 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《燃气涡轮试验与研究》2017年第6期7-11,共5页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(NSFC51076064);江苏省"六大人才高峰"第五批高层次人才项目(2008136);江苏省普通高校研究生科研创新计划资助项目(CXLX12_0152)

摘　　要：为探寻高压涡轮转子内应用射流涡流方案对原涡轮转子性能的影响,采用原高压涡轮转子模型(model-B1)和应用射流涡流方案的高压涡轮转子模型(model-B2和model-B3)两个大类进行研究,其中model-B2和model-B3用于对比分析涡轮转子叶片上有无径向凹腔对原涡轮转子性能的影响。数值模拟过程中,应用了基于压力的隐式稳态求解器,以及尺度适应模拟湍流模型(SAS)。结果表明:在涡轮转子内应用射流涡流方案,主流通道内的温度分布十分均匀,涡轮转子叶片进出口截面处的平均温度基本相等;涡轮转子叶片带径向凹腔时,应用射流涡流方案可实现涡轮内的等温燃烧过程;高压涡轮转子叶片的落压比与原涡轮转子叶片的落压比基本相等,射流涡流方案的应用不会对原有涡轮转子叶片的做功能力和做功效果造成影响。In order to investigate the effect of jet-vortex flow scheme applied in high pressure turbine on the performance of the turbine rotor,the study of the geometry model including the original high pressure turbine rotor model(model-B1),and high pressure turbine rotor model with jet-vortex flow scheme(model-B2and model-B3)was carried out to contrast analyze the effect of the turbine rotor blade with/without the radial con-cave cavity on the performance of original turbine rotor.In the process of numerical simulation,the implicit steady-state solver based on pressure,as well as the scale adapting simulation model(SAS)was applied.Re-sults show that for jet-vortex flow scheme in high pressure turbine,the temperature distribution is very uni-form in mainstream channel,the average temperature of the inlet and outlet of turbine rotor blade section is basically equal,and when the turbine rotor blade have the radial concave cavity,jet-vortex scheme can real-ize isothermal combustion inside the turbine.The pressure ratio of high pressure turbine rotor blade applicat-ed jet-vortex flow scheme is basically equal to that of original high pressure turbine rotor;the jet-vortex scheme applied has no influence on the work ability and the work effect of the original turbine rotor blade.

关 键 词：航空发动机 涡轮内增燃 射流涡流 径向凹腔 涡轮叶片 等温燃烧 数值模拟 

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]