Invention Grant
US08096768B1 Turbine blade with trailing edge impingement cooling 有权
涡轮叶片具有后缘冲击冷却

Turbine blade with trailing edge impingement cooling
Abstract:
A turbine blade for an industrial gas turbine engine, the blade includes a squealer pocket formed by a pressure side tip rail and a suction side tip rail with tip cooling holes opening onto the tip floor in the trailing edge region, a tip corner and two impingement cooling air exit slots formed between the pressure side and the suction side tip rails and the tip corner. The cooling air flowing along the tip pocket flows out the exit slots as impingement jets and provide cooling for the tip corner to prevent an over-temperature that results in erosion.
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