초록 ▼

An axial flow turbomachine has at least one circumferential row of aerofoil members in which at least one of the two end walls (33) between successive blades (30) is given a non-axisymmetric profile to modify the boundary layer flow at the wall. In one form of the profile, a convex region (33) adjac

An axial flow turbomachine has at least one circumferential row of aerofoil members in which at least one of the two end walls (33) between successive blades (30) is given a non-axisymmetric profile to modify the boundary layer flow at the wall. In one form of the profile, a convex region (33) adjacent each member pressure surface (35) and a complementary concave region (34) adjacent each member suction surface (34) extend over at least a major part of the blade chord lengths to reduce the transverse pressure gradient and thereby reduce vortical energy losses. In another form of the profile, at least one end wall (33) has complementary convex and concave regions (50,51) extending through the zone of the trailing edges of the members (30) on the suction end pressure surface sides (34,35) respectively of each member, thereby to reduce over turning of the flow. Both forms of profiling can be employed in combination.

대표청구항 ▼

[ What is claimed is:] [1.]1. 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 r

[ What is claimed is:] [1.]1. 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.