Patent ID: 6413045
Filing Date: 2002-07-02
Classification: F01D,Y02T

Abstract:
A shrouded turbine blade for use in a gas turbine device through which gases flow for compression and combustion before exiting the gas turbine device, said blade comprising an aerofoil having a shroud on its radially outer end with respect to an axis of operational rotation thereof, said shroud having a leading edge which in operation creates a pressure pattern of gases flowing over said blade including in advance of said leading edge, said pressure pattern including a region of high pressure and regions at a pressure lower than the high pressure on opposite sides of said high pressure region, said leading edge of said shroud being continuous and a forward portion shaped with a projecting portion including recessed portions on opposite sides of said projecting portion corresponding to low pressure regions in said pressure pattern and with the projecting portion corresponding to a high pressure portion of the pressure pattern relative to an adjacent array of stator vanes to confine a substantial portion of the gas flows which extend from the radially outer leading edge portion of said shroud in directions other than downstream, during in situ operational rotation of the turbine blade, said continuous leading edge of said shroud also being forwardly projected from the leading edge of the blade.