(V08BT09A062)High Pressure Turbine Rotor Stage Endwall Cooling and Passage Thermal Fields as affected by Leakage Flow and Combustor Liner Coolant Streams

摘要

The effects of an engine-representative combustor exit temperature profile and different disc cavity leakage flow rates on endwall adiabatic effectiveness distributions and passage temperature fields in a high pressure turbine rotor stage of a gas turbine are experimentally documented. The measurements aremade on a stationary linear blade row cascade with an axisymmetrically-contoured endwall of modern engine geometry and with engine-representative approach flow thermal and fluid mechanics characteristics.