Turbine Blade - Thermal Coupling Calculation And Design Optimization Of The Numerical Study

This paper presents a design for turbine blade profile via optimization. The position of cooling holes on the turbine blade was optimized using the heat-flow coupling method. The cooling method to protect the trailing edge ablated was investigated with coolant slot for high-pressure turbine vane using the method developed in this paper.In the aerodynamic optimal of turbine blade, initial blade is generated by using parametric method and Bezier curve. The Navier-Stokes equation is then used for the viscous flow calculations. The Genetic Algorithm (NSGA-II) and the NLPQL algorithm are used for exploration. By modifying the key points of the suction surface and pressure surface, the lowest pressure loss and the maximal turning angle are obtained. The results shown the method developed in this paper was effective.The normal method to compute the turbine temperature is pre-solved the temperatures on solid surfaces in contact with main flow and coolant flow, it is a risky procedure. In this paper, a new method, heat-flow coupling simulation is developed. It eliminates the need to specify the temperatures and the heat fluxes, only need to give the boundary conditions. Using this method to analyze the flow and the heat transfer inside the blade, the position of the five cooling holes is optimized to reduce the temperature of the blade.The problem of trailing edge ablated for a high-pressure turbine vane was studied in this paper using the heat-flow coupling simulation method. The results demonstrate that heat-flow coupling is more feasible compare to the adiabatic simulation. In order to protect the trailing edge ablated, coolant slot is applied in the vane. Three different cooling slots are investigated in the paper. The results show that all these slots could decrease blade temperature obviously. The maximal temperature drop is about 180 degrees.