Turbine vanes with airfoil-proximate cooling seam
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United States of America Patent
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Sep 1, 2009
Grant Date -
Feb 26, 2009
app pub date -
Jul 27, 2006
filing date -
Jul 27, 2006
priority date (Note) -
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Abstract
Aspects of the invention relate to a turbine vane in which the inner and outer platforms are located substantially entirely on either the pressure side or the suction side of the airfoil. When a plurality of such vanes are installed in the turbine, a seam is formed by the circumferential end of the inner and outer platforms and a portion of the airfoil of a neighboring vane. During engine operation, a high pressure coolant is supplied to at least one of the platforms. The coolant can leak through the seam. Because the seam is located proximate the airfoil, the coolant leakage through the seam can be productively used to cool the transition region between the vane platforms and the airfoil. In addition to such cooling benefits, aspects of the invention can result in a potential increase in engine efficiency as well as component life.
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