摘要
针对涡轮过渡段的中间机匣支板通道存在高逆压力梯度而易于诱发附面层流动分离问题,提出支板的气动优化设计方法,并开展相关的优化设计研究。结果表明,高压涡轮出口的流场结构特征对于过渡段导流支板通道的气动性能与附面层流动影响较大,考虑支板上、下游级环境条件下的气动优化设计技术是解决这一问题的一种有效途径。优化后的支板通道结构能够削弱通道的附面层流动分离的尺度与强度,不仅涡轮系统的绝热效率最大分别提升了3.13%、1%以及0.12%,而且非设计状态下涡轮系统的气动性能良好。
To the problem of boundary layer flow separation which is induced by high reverse pressure gradient in the inter-turbine-duct,an aerodynamic optimization design method for the strut is proposed and carried out in this paper.The research results indicated that the aerodynamic performance and boundary layer flow of the inter-turbine-duct are significantly affected by the flow in passage outlet of the high-pressure turbine,and the aerodynamic optimization design technology considering the flow conditions from upstream and downstream of the strut is an effective way to solve this problem.Under coupled turbine stage flow conditions,the scale and intensity of boundary layer flow separation are skillfully weaken by optimized strut in the inter-turbine-duct.It is not only the adiabatic efficiency of the turbine system is increased by 3.13%,1%,and 0.12%,respectively,but also the aerodynamic performance of the turbine system is excellent in the off-design condition.
作者
张振久
刘明俊
梁倬铭
陈焕龙
王兵
肖海兵
杨显清
ZHANG Zhenjiu;LIU Mingjun;LIANG Zhuoming;CHEN Huanlong;Wang Bing;XIAO Haibing;YANG Xianqing(Shenzhen Institute of Information Technology,Shenzhen 518172,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China;Yobow Turbofan(shenzhen)Co.,LTD,Shenzhen 518055,China)
出处
《工程热物理学报》
北大核心
2025年第4期1162-1172,共11页
Journal of Engineering Thermophysics
基金
广东教育厅高等学校科研平台和项目(No.KJ2022C010)
广东省科技计划项目(No.2021A0505030013,No.2023ZDZX3082)。
关键词
附面层分离
压力梯度
气动优化设计
流动匹配
涡轮过渡段支板
boundary layer separation
pressure gradient
aerodynamics optimization
flow matching
strut of inter-turbine-duct
作者简介
张振久(1982-),男,副教授,博士,主要从事精密加工与检测、发动机部件优化设计研究;通信作者:陈焕龙(1982-),男,副教授。E-mail:chenhuanlong@126.com。
