A Numerical Procedure To Determine Film Cooling Effects In Gas-Turbine Stator Blades Design

The continuing need to improve both efficiency and specific power of gas turbines requires progressively increasing turbine inlet temperatures and blade cooling efficiency. This paper presents a blade cooling simulation code for gas turbine stator blades analysis. A comparison between the predictions of simulation and the experimental data of the external nozzle temperatures of a small heavy duty gas turbine is presented. The simulation code allows for several cooling techniques on the basis of different solutions combined (as they often are) on the same blade. The cooling model considered is simplified: the limitation in the accuracy of the results is far overcome by the simplicity and versatility of the approach. A two-dimensional Navier Stokes simulation of film cooling is also compared with a correlation approach.