Improvement of Film Cooling Design for Turbine Vane Leading Edge Considering Combustor Outflow  

作　　者：WANG Xinyu LIU Cunliang FU Zhongyi LI Yang ZHU Huiren 

机构地区：[1]School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China [2]AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China

出　　处：《Journal of Thermal Science》2024年第1期311-327,共17页热科学学报（英文版）

基　　金：financial support from the National Natural Science Foundation of China (Grant No.U2241268);the Natural Science Foundation of Hunan Province (Grant No.2021JJ40646);the National Science and Technology Major Project(Grant No.J2019-Ⅲ-0019-0063);the Innovation Capacity Support Plan in Shaanxi Province of China (Grant No.2023-CX-TD-19)。

摘　　要：As the interaction between the combustor and the turbine in the aero-engine continues to increase,the film cooling design considering the combustor swirling outflow has become the research focus.The swirling inflow and high-temperature gas first affect the vane leading edge(LE).However,no practical improved solution for the LE cooling design has been proposed considering the combustor swirling outflow.In this paper,the improved scheme of showerhead cooling is carried out around the two ways of adopting the laid-back-fan-shaped hole and reducing the coolant outflow angle.The film cooling effectiveness(η) and the coolant flow state are obtained by PSP(pressure-sensitive-paint) and numerical simulation methods,respectively.The research results show that the swirling inflow increases the film distribution inhomogeneity by imposing the radial pressure gradient on the vane to make the film excessively gather in some positions.The showerhead film cooling adopts the laid-back-fan-shaped hole to reduce the momentum when the coolant flows out.Although this cooling scheme improves the film attachment and increases the surface-averaged film cooling effectiveness(η_(sur)) by as much as15.4%,the film distribution inhomogeneity increases.After reducing the coolant outlet angle,the wall-tangential velocity of the coolant increases,and the wall-normal velocity decreases.Under the swirl intake condition,both ηand the film distribution uniformity are significantly increased,and the growth of η_(sur) is up to 16.5%.This paper investigates two improved schemes to improve the showerhead cooling under the swirl intake condition to provide a reference for the vane cooling design.

关 键 词：turbine vane showerhead cooling swirling inflow laid-back-fan-shaped hole film hole inclination 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]