三维内并联TBCC进气道模态转换过程气动特性研究  

Aerodynamic characteristics of an over/under turbine based combined cycle inlet mode transition process

作　　者：袁永青 徐腾宏 叶巍 YUAN Yongqing;XU Tenghong;YE Wei(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China;Nanjing Pu Guo Science Technology Co.,Ltd,Nanjing 210000,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500 [2]南京普国科技有限公司,南京210000

出　　处：《燃气涡轮试验与研究》2023年第5期1-10,共10页Gas Turbine Experiment and Research

摘　　要：对一种典型的三维内并联TBCC进气道在模态转换过程中的稳态气动特性进行了数值模拟,探索了分流板分别处于冲压通道关闭、模态转换初始位置、涡轮通道关闭以及中间位置上时进气道的气动性能。重点分析了进气道出口的马赫数、流量、总压恢复系数、畸变指数等参数随出口反压的变化规律。结果表明:冲压通道和涡轮通道各自内部的结尾激波被推出分流板以前,通道出口反压变化对另外一个通道出口参数的影响较小;但是由于其中一个通道的结尾激波的变化,可能会在出口反压增加到某一数值后,另外一个通道的畸变指数发生突增。研究结果可以为TBCC进气道模态转换过程中的性能分析提供方案参考。Numerical simulation of the mode transition process of a typical over/under Turbine Based Combined Cycle(TBCC)inlet under steady flow conditions was carried out.The aerodynamic characteristics were explored,which included the turbo mode,the ram mode,and the splitter situated in the middle place.Special stress was made on analyzing the changing rules of inlet performance parameters under different backpressure,including Mach number,mass flow,total pressure recovery coefficient,and distortion parameter.Research results show that the backpressure change of one passage has little influence on the outlet performance of another passage.But distortion coefficient increases suddenly sometimes when outlet backpressure reaches a certain value for different location of terminal shock wave.Results of the research would provide reference for the performance analysis of TBCC inlet mode transition process.

关 键 词：涡轮基组合循环发动机(TBCC) 进气道 气动特性 模态转换 结尾激波 流量分配 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]