Reynolds Stress Transport Modeling Of Film Cooling At The Leading Edge Of A Symmetrical Turbine Blade Model

摘要

This paper investigates the performance of the SSG (Speziale, Sarkar, and Gatski) Reynolds Stress Model for the prediction of film cooling at the leading edge of a symmetrical turbine blade model using the CFX 5.7.1 package from ANSYS, Inc. Using a finite-volume method, the performance of the selected turbulence model is compared to that of the standard k-ε model. The test case blade model is symmetric and has one injection row of discrete cylindrical holes on each side near the leading edge. Numerical simulations are conducted for three different blowing ratios; film cooling effectiveness contours on the blade surface and lateral averaged adiabatic film cooling effectiveness are presented and compared with available measurements. The computations with the standard k-ε model reproduce the well-known underpredieted lateral spreading of the jet, and, consequently, lower values of the lateral averaged adiabatic film cooling effectiveness has been obtained. On the other hand, the second order Reynolds Stress Model yields reasonably good agreement with measurement data. In addition to validation data, several longitudinal and transversal contours and vector planes are reproduced and clearly underscore the anisotropic turbulent field occurring in the present shower head film cooling configuration.