Impact of Different Film-Cooling Modes at Leading Edge on the Aerodynamic and Heat Transfer Performance of Heavy Duty Gas Turbine

In this paper, the leading edge film-cooling flow field of a heavy duty gas turbine cascade has been studied by central difference scheme and multi-block grid technique. The research is based on the three-dimensional N-S equation solver. By way of comparison and analysis of the temperature field, the distribution of profile pressure, and the distribution of film-cooling adiabatic effectiveness in the region of leading edge with different cool air mass and injection angles, it is found that the aerodynamic energy loss drops a little by adding the cool air, the distribution of temperature of the blade is obviously changed and the adiabatic effectiveness at the leading edge and suction side is higher than that on pressure side. Profile pressure is not changed obviously in the whole, with the exception in the local region near the cooling holes. The change of the pressure variation is greater on the suction side. The influence of the change of cool air mass and injection angles on the flow field near the leading edge is obviously.