Aerodynamic and End-Wall Film Cooling Investigations of a Gas Turbine Nozzle Guide Vane Applying Temperature-Sensitive Paint

This paper presents endwall film cooling investigations with a single row of fanshaped holes in a low-speed, six-bladed linear cascade. The variation of the cascade loading was achieved by changing the incidence. The investigated profile is based on a nozzle guide vane of a highly loaded gas turbine. The aerodynamic performance was investigated using pneumatic probes. The film-cooling effectiveness distribution is determined using the temperature-sensitive paint technique (TSP). Carbon dioxide was used as coolant to provide elevated density ratios of about 1.4. Although low thermal conductivity material is used for the endwall test plate, the measured temperature fields show influences of 3D heat conduction inside the test plate. To measure film effectiveness and the heat transfer separately, an adiabatic test surface is needed. Therefore the effects of heat conduction are modeled using the FE-method. With the resulting convective heat flux pattern derived from the computations, the endwall film cooling measurements are corrected. Furthermore this approach is applied to evaluate the heat loss inside the holes and the film discharge temperature at the hole exit.