Progress of Film-cooling Turbine Numerical Simulation Technology

Inlet gas temperature of the high pressure turbine is increasing as aircraft engine performance improving, which is much higher than metal endurable temperature. So cooling technology is used in turbine for working safety. Film-cooling, with high cooling efficiency and easy realization, is widely applied in aircraft engines. However, for the usage of large mass flow cooling air and the complexity of mixing with main gas flow, how to simulate the mixing process become a key step of design in cooling turbine. In this paper, the developments of source term method and real film hole method were expatiated, the two methods were widely used in film-cooling turbine aerodynamic simulation. The advantages, disadvantages and engineering application status of the two methods were summarized, and the next research directions in engineering application were suggested.