초록 ▼

An axial compressor has at least one circumferential row of aerofoil members (30a, 30b, 30c) in which at least one of the two end walls (37) between adjacent blades is given a non-axisymmetric profile, defined by circumferentially-extending sinusoids at a number of axial positions (AA, BB, CC). Corr

An axial compressor has at least one circumferential row of aerofoil members (30a, 30b, 30c) in which at least one of the two end walls (37) between adjacent blades is given a non-axisymmetric profile, defined by circumferentially-extending sinusoids at a number of axial positions (AA, BB, CC). Corresponding points on the successive sinusoids are joined by spline curves, so that the curvature of the end wall is smooth. This end-wall profiling modifies the boundary layer flow at the wall, reducing or eliminating the corner separation and reversed flow associated with known arrangements.

대표청구항 ▼

I claim: 1. A row of aerofoil members for an axial compressor, the row comprising: a plurality of radially extending aerofoils; and circumferentially extending radially inner and outer end walls, wherein at least one of the end walls has a profile defined by a plurality of perturbations at a succes

I claim: 1. A row of aerofoil members for an axial compressor, the row comprising: a plurality of radially extending aerofoils; and circumferentially extending radially inner and outer end walls, wherein at least one of the end walls has a profile defined by a plurality of perturbations at a succession of axial positions, wherein at least a first terturbation is not in phase with a second perturbation, wherein at least one of the perturbations is a sinusoid, the or each sinusoid being defined by its phase and its amplitude relative to the baseline profile of the or each end wall, the pitch of the or each sinusoid being the same as the pitch of the aerofoil members, the or each end wall being further shaped to provide smooth transitions between successive perturbations. 2. The row of aerofoil members as in claim 1, wherein the at least one sinusoidal perturbation is additionally defined by a constant displacement relative to the baseline profile of the or each end wall. 3. The row of aerofoil members as in claim 1, wherein a concave region is provided in at least one end wall upstream of the perturbations in that end wall. 4. The row of aerofoil members as in claim 1, wherein the further shaping of the or each end wall is achieved by fitting a plurality of spline curves between points on successive perturbations in a streamwise direction. 5. The row of aerofoil members as in claim 1, wherein the amplitude of each sinusoidal perturbation is less than 10% of the true chord length of the aerofoil members. 6. The row of aerofoil members as in claim 1, wherein the amplitude of each sinusoidal perturbation is between 1% and 6% of the true chord length of the aerofoil members. 7. The row of aerofoil members as in claim 1, wherein at least one of the profiled end walls is formed by surfaces of platforms that are integral with the members of the row. 8. The row of aerofoil members as in claim 1, wherein the members project from a rotary hub and are provided with an outer circumferential shroud rotatable with the members and forming an outer end wall, and in which at least the outer end wall is profiled. 9. The row of aerofoil members as in claim 1, wherein both the inner and the outer radial end walls are profiled. 10. The row of aerofoil members according to claim 1, wherein the profile extends beyond at least one of the leading and trailing edges of the members. 11. The row of aerofoil members as in claim 1, wherein the member has an integral portion extending transversely to the pressure and suction surfaces at least at one radial end of the member to form at least a portion of an end wall. 12. A row of aerofoil members for an axial compressor, the row comprising: a plurality of radially extending aerofoils; and circumferentially extending radially inner and outer end walls, wherein at least one of the end walls has a profile defined by a plurality of perturbations at a succession of axial positions, at least one of the perturbations being a sinusoid, the or each sinusoid being defined by its phase and its amplitude relative to the baseline profile of the or each end wall, the pitch of the or each sinusoid being the same as the pitch of the aerofoil members, the or each end wall being further shaped to provide smooth transitions between successive perturbations, and wherein a concave region is provided in at least one end wall upstream of the perturbations in that end wall.