Patent ID: 6454526
Filing Date: 2002-09-24
Classification: F01D,F05D

Abstract:
A combustion turbine vane assembly comprising:an outer endcap having a plurality of generally straight cooling passages and passage segments therethrough; an inner endcap having a plurality of generally straight cooling passages and passage segments therethrough; a vane casting having an outer shroud, an airfoil, and an inner shroud; said outer shroud, airfoil and inner shroud each having a plurality of generally straight cooling passages and passage segments and wherein all said straight cooling passages and passage segments are in fluid communication, wherein said airfoil cooling passages extend from said outer shroud to said inner shroud; wherein said outer endcap is coupled to said outer shroud so that all said outer endcap cooling passages, said outer shroud cooling passages and airfoil cooling passages are in fluid communication; and said inner endcap is coupled to said inner shroud so that all said inner end cap cooling passages, said inner shroud cooling passages and airfoil cooling passages are in fluid communication.