Patent ID: 6811378
Filing Date: 2004-11-02
Classification: F01D,F05B,F05D

Abstract:
A turbine blade, comprising:a root portion having a cooling fluid cavity therein; a platform connected to said root portion; an airfoil portion extending from said platform, said airfoil portion including at least one cooling passageway extending substantially radially through said airfoil, and at least one cooling hole extending substantially radially through said airfoil, said at least one cooling passageway and said at least one cooling hole each defined by an inner wall and having an inlet for receiving a flow of cooling fluid from said cavity; a shroud projecting outwardly from said airfoil and having a radially inward facing surface, a radially outward facing surface, and a shroud edge extending therebetween, at least one cooling fluid outlet adjacent said edge, and at least one cooling passage between said radially inward facing surface and said radially outward facing surface, said at least one cooling passage approximately parallel to said radially inward facing surface; a tube located within said cooling passageway, said tube having an outer wall, a first end adjacent said inlet and a second end radially outward therefrom, said cooling passage communicates with said inlet through said tube; and, standoff means for maintaining said inner wall of said cooling passageway in spaced relation to said outer wall of said tube to minimize heat transfer between the airfoil and the tube.