Trailing Edge Film Cooling in a Transonic Cascade – Aerodynamic Experiments and Evaluation of Airfoil Loss Coefficients (European Research Project AITEB-2)

Kurzfassung

This report documents results from aerodynamic experiments in a linear cascade consisting of high pressure turbine blades with three different trailing edge cooling configurations. The investigations are part of Work Package 2 of the 6th European Framework Project AITEB-2 and were performed in the transonic cascade wind tunnel at DLR. Airfoil loss coefficients were evaluated from the results showing the impact of different trailing edge cooling ejection on the aerodynamic performance of the cascade.