| 摘要 |
A gas turbine airfoil (e.g. 12 ) includes a pressure sidewall ( 14 ) and a suction sidewall ( 16 ) joined along respective leading and trailing edges ( 18, 20 ) and extending radially outward from an inner diameter ( 26 ) to an outer diameter ( 22 ). The airfoil includes a plurality of suction side flow channels ( 52 ) extending chordwise within the suction sidewall and having respective heights selected to achieve a desired degree of cooling for the suction sidewall. The airfoil also includes a plurality of pressure side flow channels ( 30 ) extending chordwise within the pressure sidewall and having respective heights selected to achieve a desired degree of cooling for the pressure sidewall. A transition region ( 58 ) is provided in each flow channel wherein the height of the channel is reduced to an outlet height so that respective outlets of the flow channels can each be independently disposed in the trailing edge.
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