Effects of trailing edge film cooling on the aerodynamic performance of a nozzle vane cascade

The aerodynamic performance of a gas turbine nozzle vane cascade with and without a cooled pressure side and trailing edge was investigated. Tests were conducted for variable cascade operating conditions (M2is = 0.2-0.6) and coolant injections (MFR = 0.0-3.0%). Detailed boundary layer and wake traverses as well as secondary flows measurements in a downstream plane were performed allowing to draw a comprehensive picture of cascade performances. Results were compared to the solid vane case without any film cooling. Coolant injection was found to marginally influence the cascade performances; more significant differences were related to the cooling system geometry