Patent ID: 8192153

Claim:
A circumferential row of aerofoil members which, in use, span an annular duct for carrying a flow of compressible fluid, the duct being centred on a rotational axis of a turbomachine, the row comprising aerofoil members, each aerofoil member having a pressure surface and a suction surface, wherein pressure and suction surfaces of neighbouring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid, and the row comprises a radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal, wherein each aerofoil member has reverse compound lean, and further has a leading edge which has a position at the radial endwall which is upstream of its position at midspan, wherein the radial endwall at each sectoral passage has a non-axisymmetrical cross-section formed by a region that, in meridional section, is convexly profiled immediately adjacent the pressure surface and a region that, in meridional section, is concavely profiled immediately adjacent the suction surface, wherein the axial chord of the aerofoil section of the aerofoil member at the endwall is in the range of from 5% to 30% longer than the axial chord of the aerofoil member at midspan, and wherein, with increasing distance from the endwall, the leading edge travels downstream until, at a distance along the leading edge from the endwall which is in the range of from 10% to 100% of the total distance along the leading edge from endwall to midspan, the leading edge is at the same streamwise position that it assumes at midspan.