In order to numerically simulate the viscous flow field in turbine stage with cooling gas injection

Jameson's Finite Volume Methods are employed to solve Reynolds averaged Navier-Stokes Equations on H-H type structural grid generated with elliptical method.For the simplicity and robustness of the software

Baldwin-Lomax algebraic model is chosen for turbulence closure.According to the so called One-Dimension Isentropic Flow model

the mass

momentum

and energy flux injected through film cooling holes or slots to flow field are computed and then coupled to the boundary conditions to reveal the effects of cooling gas.Using of Mixing Plane model makes the simulation of stator-rotor interaction be realized with acceptable computer resource costs.A typical configuration-C3x cascade with film cooling

which has experimental data

is computed to validate the present methods.Results of both flow field parameters and heat transfer parameters are in good agreement with experimental data.To illustrate the present methods' capability of handling configurations with engineering complexity

simulation results of two realistic turbine stages

a transonic one and a subsonic one

both with complex layout of cooling holes and slots

are presented.