Study On The Influence Of Film Cooling Structure On The Cooling And Aerodynamic Performance Of High Press Turbine Vane

Aviation gas turbines directly provide power to aviation aircraft,and their performance reflects the advanced level of aviation industry development.As one of the three core components of a gas turbine,the performance of the turbine directly affects the performance of the complete machine.As the performance indicators of gas turbine(such as gas turbine efficiency and thrust-to-weight ratio)continues to increase,the thermal load of turbine components is also increasing,which gives a severe challenge to blade materials.In order to ensure the safety and reliability of turbine blades,efficient turbine cooling technology must be developed.In this paper,cooling structures are designed for the first stage vane of a gas turbine,the studied vane was straight vane,which was stretched from the mid-span vane shape of the real vane.According to the working environment,different kinds of cooling structures are designed and gas-thermal coupling calculation is carried out,the results are analyzed for flow and heat transfer.In the design,the high-temperature working environment of the studied vane and the distribution of the coolant are considered.In order to achieve higher cooling efficiency and aerodynamic efficiency,double wall structures are designed for the vane,and the combined cooling method of film cooling,impact cooling and enhanced cooling by the flow column are introduced.In this paper,the film cooling structure of the vane leading edge are studied.The results show that when the radial jet angle of the inline film holes is 45° and pointed to the tip of the vane,the cooling performance is the best;When the film holes are staggered arranged,the cooling performance is worse.In this paper,the film cooling structure of the mid-chordwise is studied.The results show that when the film silts of the pressure side are equipped with sleeve structures while the film silts of the suction side have no sleeve structures,the cooling performance is the best.But it also cost a little more coolant,and the aerodynamic efficiency is lost slightly.In this paper,a best vane cooling structure is designed,the calculated temperature field distributions are reasonable,and the coolant distribution is applicable for the heat transfer requirements.