59418 - A Method of Solving Three Temperature Problem of Turbine With Adiabatic Wall Temperature 

The new structure of aeroengine turbine cavity makes the turbine component obtain better cooling effect, but the complex design of inlet and outlet makes it difficult to determine the heat transfer reference temperature of turbine disk. In this paper, the three-temperature problem of a rotating cavity with two cross inlets are studied by means of experiment and numerical simulation. By substituting the adiabatic wall temperature for the inlet temperature and summarizing its variation law, the problem of selecting the reference temperature of the multi inlet cavity can be solved. The results show that the distribution of the adiabatic wall temperature is divided into the high jet area and the low inflow area, which are mainly affected by the turbulence parameters λ_T, the rotating Reynolds number Re_ω, the high inlet temperature T_f,H^* and the low radius inlet temperature T_f,L^* of the inflow, while the partition position r_d can be considered only related to the turbulence parameters λ_T and the rotating Reynolds number Re_ω of the inflow. In this paper, based on the analysis of the numerical simulation results, the calculation formulas of the partition position r_d and the adiabatic wall temperature distribution are obtained. The verification results show that the method of experiment combined with adiabatic wall temperature zone simulation can effectively solve the three-temperature problem of rotating cavity.