Patent ID: 6283713
Filing Date: 2001-09-04
Classification: F01D,Y10S

Abstract:
A circumferential row of generally radially extending aerofoil members for location in an annular duct of a turbomachine for a flow of a compressible fluid through sectoral passages bounded by respective pressure and suction surfaces of adjacent aerofoil members, said row comprising at least one radial end wall, said at least one radial end wall in each said passage between said surfaces having a non-axisymmetrical cross-section formed by a convex profiled region immediately adjacent the aerofoil member pressure face and a concave profiled region immediately adjacent the aerofoil member suction face, said regions extending over at least the major part of the chord of the respective aerofoil members, whereby to reduce the pressure gradient in the flow over said end wall in a direction transverse to the passage.