Abstract
The trailing edge tip region has always been the most vulnerable part of high-pressure turbine blade. The requirements for both aerodynamic efficiency and cooling effectiveness make it a challenging task in turbine blade cooling design. A closely combined experimental and CFD effort, specifically focusing on trailing edge region, is reported in the present study. High-resolution transient thermal measurement data were obtained from a transonic wind tunnel and used to validate the CFD solver employed. Two different trailing edge cooling configurations were evaluated and their associated aerothermal characteristics were discussed. Due to the strong “wiping effect” from the high pressure mainstream flow, cooling the pressure side cutback tip is not efficient. In comparison, the suction side cutback configuration can be better cooled. Protected by the pressure side rim, the coolant coverage on the cavity floor can be extended to the end of the trailing edge. Additional cooling schemes are required to keep the pressure side rim survive for all cutback configurations studied.
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