| 摘要 |
<p>PROBLEM TO BE SOLVED: To provide a gas turbine airfoil with cooling enhancement.SOLUTION: A turbine vane segment includes one or more vanes extending between a radially inner side wall and a radially outer side wall, each vane having a peripheral edge wall extending between a leading edge and a trailing edge of the vane. In one exemplary embodiment, at least one substantially radially-oriented cooling channel is formed in the peripheral edge wall at the leading edge, with openings at opposite ends of the cooling channel. The location and length of the cooling channels may vary about the peripheral edge wall, and the inner cavity of the vane may be provided with ribs extending along the one or more cooling channels to reinforce the wall and to also increase the cooling surface area in the inner cavity.</p> |
