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US 6,283,713 B1Granted
Bladed ducting for turbomachinery
AssigneeROLLS-ROYCE plc
InventorsNeil W Harvey, Martin G Rose
Life of this patent
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AssigneeROLLS-ROYCE plc
InventorsNeil W Harvey, Martin G Rose
Estimating the term…
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.
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.
A circumferential row of generally radially extending aerofoil members for location in an annular duct of the turbomachine for a flow of 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 of each said passage between said aerofoil member surfaces having, in a region extending through the zone of the trailing edges of the members, a non-axisymmetric cross-section formed by a raised convex profiled region adjacent the suction surface and a depressed concave profiled region adjacent the pressure surface, each convex region forming an acute-angled junction with the member suction surface.
A circumferential row of generally radially extending aerofoil members for location in an annular duct of the turbomachine for a flow of 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 wall of each said passage between said aerofoil member surfaces having, in a region extending through the zone of the trailing edges of the members, a non-axisymmetric cross-section formed by a raised convex profiled region adjacent the suction surface and a depressed concave profiled region adjacent the pressure surface, each concave region forming an obtuse-angled junction with the member pressure surface.
Dependencies are inferred from the claim text.