Specifics of Film Cooling Formation on the Turbine Blade Suction and Pressure Sides when Using Heat Exchange Intensifiers under Conditions of Accelerated Main Flow and Wall Curvature

摘要

The article presents experimental data on the formation of film cooling on the suctions and pressure sides of a turbine blade near its leading edge under conditions of flow acceleration and wall curvature using V-shaped grooves behind the injection holes. It is shown that to achieve acceptable values of the efficiency of film cooling when using V-shaped grooves on the wall, a lower relative flow rate of the cooler can be used. The results can be used in the design of effective cooling systems for turbine blades.