大扩张角涡轮过渡段非定常流动数值仿真  

Numerical Simulation of the Unsteady Flow of an Aggressive Intermediate Turbine Duct

作　　者：蒋首民 张海华 王雷 陈云 马广健 JIANG Shou-min;ZHANG Hai-hua;WANG Lei;CHEN Yun;MA Guang-jian(AECC Shenyang Engine Research Institute,Shenyang 110015,China;Engine Affairs Military Representatives Office of Navy in Shenyang Area,Shenyang 110031,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]海装沈阳局,沈阳110031

出　　处：《航空发动机》2019年第5期36-41,共6页Aeroengine

基　　金：国防工程重点研究项目资助

摘　　要：为进一步减小涡轮过渡段流动损失,深入了解涡轮过渡段中的非定常损失机理,开展了大扩张角过渡段研究。在过渡段的非定常流动机理研究中,过渡段进口流场的最显著特点是:转子泄漏涡、通道涡和尾迹。采用数值方法对大扩张角涡轮过渡段进行3维非定常数值仿真。结果表明:支板尾缘部分的静压波动小于支板前缘部分的;高压涡轮静子尾迹被转子切割后进入转子通道中向下游传播并在过渡段内形成尾迹通道,尾迹在过渡段内的时空演化是过渡段内损失的主要来源;过渡段支板表面负荷分布发生明显的周期性变化,支板表面承受较强的非定常力,在过渡段设计中必须考虑。In order to further reduce the flow loss in the intermediate turbine duct and understand the mechanism of unstable loss in the intermediate turbine duct,an aggressive intermediate turbine duct was studied.In the study of the unsteady flow mechanism in the intermediate turbine duct,the most significant characteristics of the inlet flow field in the intermediate turbine duct were the rotor leakage vortex,the passage vortex and the wake.Three-dimensional unsteady numerical simulation was carried out for the aggressive intermediate turbine duct by numerical method.The results show that the static pressure fluctuation in the trailing-edge of the branch plate is smaller than that in the front-edge of the branch plate.The high pressure turbine stator wake is cut by the rotor and propagates downstream into the rotor passage and forms a wake passage in the intermediate turbine duct.The temporal and spatial evolution of wake in the intermediate turbine duct is the main source of loss in the intermediate turbine duct.There are obvious periodic changes in the surface load distribution of the support plate in the intermediate turbine duct,and the surface of the support plate bears a strong irregular force,which must be considered in the design of the intermediate turbine duct.

关 键 词：非定常流动 大扩张角 涡轮过渡段 涡系结构 航空发动机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]