Investigation of the Wake Mixing Process behind Transonic Turbine Inlet Guide Vanes with Trailing Edge Coolant Flow Ejection DLR CONTRIBUTION TO THE FINAL REPORT

Abstract

Plane cascades consisting of transonic turbine inlet guide vanes with trailing edge coolant ejection were tested in the plane cascade facility at DLR Goettingen, (EGG). The performances of two different trailing edge configuratjions, i.e. pressure side coolant ejection versus ejection through the trailing edge were comparaed with each other. Schlieren pictures were taken, blade profile pressure distributions were determined and wake measurements were carried out with a wedge-type probe. Hot film probes were applied in the wake to qualitatively determine the turbulence and gasanalysis in combination with carbondioxide coolant ejection elucidated the wake mixing process.