级环境条件下某涡轮过渡段支板气动优化研究

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.