应用射流涡流燃烧结构方案的高压涡轮导向器性能分析与研究  

The performance analysis and research of high pressure turbine nozzle with jet vortex combustion structure

作　　者：郑海飞[1] 唐豪[2] ZHENG Hai-fei;TANG Hao(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》2018年第3期22-26,52,共6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：采用两大类模型,对应用射流涡流燃烧结构方案的高压涡轮导向器性能进行数值模拟研究。利用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),完成了涡轮内增燃燃烧室内的流动与燃烧过程的数值模拟。研究结果表明:无论是在高压涡轮导向器顶部还是在底部耦合驻涡凹腔,对导向器叶间流场形态、流体流动转折角、导向器叶间静压力场的形态以及分布、总压损失均无明显影响,维持了原有导向器的基本性能;高压涡轮导向器耦合射流涡流燃烧结构,增加了涡轮叶片叶间的平均温度以及涡轮导向器出口的平均温度。Two kinds of models were used to simulate the performance of high pressure turbine guide withjet vortex combustion structure. In the numerical simulation of the flow and combustion process of the com-bustion chamber in the turbine, an implicit steady-state solution based on pressure and the scale adaptivesimulation turbulence model（SAS） were adopted. The results show that either at the top or at the bottom inhigh pressure turbine guide coupling in vortex concave cavity, the flow field between the guide blade shape,flow turning angle, guide between leaf morphology and distribution of static pressure force field, total pres-sure loss are of no big impact, and the basic properties of the original guide is maintained; The coupled jetvortex combustion structure of high pressure turbine guide increases the average temperature of turbineblade and the average temperature of turbine nozzle outlet.

关 键 词：航空发动机 高压涡轮导向器 涡轮内增燃 射流涡流 径向凹腔 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]