Design Of Blade Profile And Cascade For Heavy Duty Gas Turbine Compressor Blade

Power industry is the basis for national economic development. In order to improve the efficiency of thermal power generation and adjust the energy structure, the state vigorously introduce and develop the gas turbine generator unit and related technologies. With the increase of heavy duty gas turbine in the share of the power industry, the localization of blade profile and cascade of the transonic compressor blade has important significance. The main research work of this paper is:1) Numerical simulation analysing of traditional NACA65 (National Advisory Committee for Aeronautics). Using the curve method to modify its profile design based on the simulation results, explore and validate the method of compressor blade airfoil design and its processes.2) Studying the transonic airfoil working characteristics and requirements, Bezier curve design leaf type and down-type line, based around an elliptical arc edge profile. After numerous attempts to generate a variety of transonic airfoil, four typical models of which make a detailed analysis and comparison of the aerodynamic simulation. The following rules:in transonic flow, curved airfoil easier to produce oblique shock wave, and the pressure distribution is more balanced and stable, hard to produce boundary layer separation. The position of the maximum thickness position can affect the shock wave generating position. The position of the maximum thickness through the shift in a certain range, the shock can be shifted with the following.3) Improving the cascade hydrostatic pressure ratio, reducing the loss factor of the target, the speed characteristics and power angle characteristics simulation of these four types of transonic airfoil cascade are compared. The following rules:in the transonic cascade, the speed characteristic, with the mach number decreased, the hydrostatic pressure ratio increases after the first rise, the total pressure recovery coefficient decreased, the loss factor gradually increased and smooth. The attack angle characteristic performance from negative to positive, the static pressure ratio increased first down and then decline steadily, the total pressure recovery coefficient first increased steadily and then decline, the loss factor through the first fall and then rise steadily.In this paper, after a lot of simulations and designs, a smaller airfoil thickness and curvature of the upper and lower profile are larger, the maximum thickness of the airfoil rearward position, namely the Fourth airfoil design result, which meets the needs of the heavy work transonic gas turbine compressor blades.