Patent ID: 8888442
Filing Date: 2014-11-18
Classification: F01D,F05D,Y10T

Abstract:
1. A turbine vane ring for a gas turbine engine having an axis, the turbine vane ring comprising a radially outer annular shroud and a radially inner annular shroud concentrically disposed about the axis and defining therebetween an annular gaspath for channelling combustion gases, a plurality of circumferentially spaced-apart airfoil vanes extending radially across the gaspath between the radially outer and the radially inner annular shrouds, each airfoil vane extending chordwise between a leading edge and a trailing edge, said radially outer shroud having a circumferentially continuous cylindrical wall extending axially from a leading edge to a trailing edge, the cylindrical wall having a radially outer surface and an opposed radially inner surface defining a flowpath boundary of the gaspath, and a first set of circumferentially distributed stress relieving slots defined in the leading edge of the cylindrical wall at locations adjacent to the leading edge of at least some of said airfoil vanes, the stress relieving slots extending radially through the cylindrical wall from the radially inner surface to the opposed radially outer surface thereof.