Process and analysis of cooling structure design for gas turbine rotor blades with film cooling

To design a reasonable cooling structure for gas turbine rotor blades with film cooling, a set of design procedure was used to complete the design of structure. Two different topologies of the cooling structures were compared by pipe-net calculation and three-dimensional temperature field calculation. The effect of different cooling structures was analysed. Then the optimum structure was used for the detailed design. The results show that for the turbine rotor blades with film cooling in the leading edge, it is better to using the middle chamber as the second inlet and the trailing edge as outlet than the rear one with the trailing edge as outlet. By using this design process, the cooling structure can be quickly designed and evaluated. Meanwhile the detail design can be conducted on this schematic design which will meet the requirements of multiple programs and rapid cooling structure design. After the process, the maximum temperature of the cooling structure is 1 188.15 K, the average temperature is 1 067.10 K, and the cooling efficiency is 0.647.