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Turbine rotor airfoil and corresponding method for reducing pressure loss in a cavity within a blade
Turbine rotor airfoil and corresponding method for reducing pressure loss in a cavity within a blade
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机译:涡轮转子翼型和相应的方法,用于减少叶片内腔内的压力损失
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摘要
A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.
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