Patent ID: 9200535
Filing Date: 2015-12-01
Classification: F01D,F05D

Abstract:
1. An aerofoil blade or vane for the turbine of a gas turbine engine, the blade or vane including: an aerofoil body comprising a base end, a trailing edge, a leading edge and an internal space and which, in use, extends radially across a working gas annulus of the engine, a coolant inlet being formed at the base end of the aerofoil body for entry of a flow of cooling air into the internal space, a corresponding coolant exhaust being formed at the trailing edge of the aerofoil body for the flow of spent cooling air from the internal space, and a passage within the internal space determining the route of cooling air and connecting the inlet to the exhaust, a first wall of the passage comprising a fence within the internal space, the fence extending at an acute angle to a radial line at the trailing edge from a start position at the base end of the aerofoil body adjacent the trailing edge to an end position in a mid-region of the internal space, and a second wall of the passage extending around the fence at an acute angle to the radial line at the trailing edge, the second wall extending substantially parallel to the fence from a start position at the base end of the aerofoil body on a first side of the fence to the mid-region of the internal space, and extending substantially parallel to the fence from the mid-region to an end position on a second side of the fence, the end position of the second wall being adjacent the base end and the trailing edge, wherein the passage loops around the fence thereby routing cooling air from the inlet first towards the leading edge of the aerofoil body and then turning the cooling air back towards the trailing edge exhaust.