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HYBRID COOLING SCHEMES FOR AIRFOILS OF GAS TURBINE ENGINES
HYBRID COOLING SCHEMES FOR AIRFOILS OF GAS TURBINE ENGINES
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机译：燃气轮机机翼的混合冷却方案
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摘要
Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a first platform and a second platform, a first platform feed cavity defined by the first platform, a second platform exit cavity defined by the second platform, a first hybrid skin core cooling cavity passage formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.
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