A gas turbine blade having a shroud extending outwardly from the tip of the airfoil portion of the blade. The shroud is cooled by cooling air passages formed within it. A radial cooling air supply hole directs cooling air directly from the blade root through the airfoil and to the shroud. A plurality of cooling air passages extend from the supply hole and are disposed adjacent bearing surfaces along which the shroud contacts the shroud of an adjacent blade. One of these cooling air holes is formed in the portion of the shroud that projects from the convex surface of the airfoil and another one of the cooling air holes is formed in the portion of the shroud that projects from the concave surface of the airfoil. The cooling air holes extend to the edge of the shroud and discharge the cooling through an opening in the edge.
申请公布号
WO9613654(A1)
申请公布日期
1996.05.09
申请号
WO1995US12653
申请日期
1995.10.02
申请人
WESTINGHOUSE ELECTRIC CORPORATION
发明人
DORRIS, ROBERT, A.;NORTH, WILLIAM, E.;MALANDRA, ANTHONY, J.