| 摘要 |
A gas turbine airfoil ( 10 ) includes a pressure sidewall ( 12 ) and a suction sidewall ( 14 ) joined along respective leading ( 16 ) and trailing edges ( 18 ) and extends radially outward from a root ( 20 ) to a tip ( 22 ). The airfoil also includes a trailing edge corner ( 24 ) comprising a metering hole ( 36 ) receiving a cooling fluid flow ( 26 ) from an interior fluid flow channel (e.g., 32 ) and discharging a metered flow ( 40 ). A dispersion cavity ( 42 ) receives the metered flow and discharges a dispersed flow ( 44 ). The dispersion cavity includes a cross sectional area ( 46 ) greater than a cross sectional area ( 48 ) of the metering hole. An open flow channel ( 52 ) receives the dispersed flow and conducts the dispersed flow to a periphery ( 54 ) of the airfoil, the open flow channel controlling mixing of the cooling fluid flow with a process gas (e.g., 28 ) flowing around an exterior ( 34 ) of the airfoil.
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