Inviscid numerical simulation of unsteady flow in turbine stage with inlet temperature distortion

The unsteady flow in turbine stage with inlet temperature distortion was studied by using Jameson's four-order Runge-Kutta scheme. Numerical simulation for unsteady flow of one-stage turbine blade rows was performed. Simulation results show that the pressure distribution on the blade and flow field in the cascade are subject to periodical variation because of relative movement of blade rows. When there is temperature distortion at the turbine stage's inlet, the temperature field in the stage passage is greatly changed. The hotter gas in the hot streak will migrate to the pressure surface of rotor, which produces the hot spot on the pressure surface of rotor to make the surface temperature of moving blade vary greatly. The effect of hot streak on flow field in the stator cascade is on the small side, but that in the moving blade row is considerable.