COMPUTATIONAL PREDICTION OF HEAT-TRANSFER TO GAS-TURBINE NOZZLE GUIDEVANES WITH ROUGHENED SURFACES

The local Mach number and heat transfer coefficient over the aerofoil surfaces and endwalls of a transonic gas turbine nozzle guide vane hav e been calculated. The computations were performed by solving the time -averaged Navier-Stokes equations using a fully three-dimensional comp utational code (CFDS), which is well established at Rolls-Royce. A mod el to predict the effects of roughness has been incorporated into CFDS and heat transfer levels have been calculated for both hydraulically smooth and transitionally rough surfaces. The roughness influences the calculations in two ways; first the mixing length at a certain height above the surface is increased; second the wall function used to reco ncile the wall condition with the first grid point above the wall is a lso altered. The first involves a relatively straightforward shift of the origin in the van driest damping function description, the second requires an integration of the momentum equation across the wall layer . A similar treatment applies to the energy equation. The calculations are compared with experimental contours of heat transfer coefficient obtained using both thin-film gages and the transient liquid crystal t echnique. Measurements were performed using both hydraulically smooth and roughened surfaces, and at engine-respresentative Mach and Reynold s numbers. The heat transfer results are discussed and interpreted in terms of surface-shear flow visualization using oil and dye techniques .