IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0036371
(2008-02-25)
|
등록번호 |
US-8192153
(2012-06-05)
|
우선권정보 |
GB-0704426.6 (2007-03-08) |
발명자
/ 주소 |
- Harvey, Neil William
- Stokes, Mark Richard
- Bagshaw, David Andrew
|
출원인 / 주소 |
|
대리인 / 주소 |
McCormick, Paulding & Huber LLP
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
46 |
초록
▼
A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centered on the axis of a turbomachine. Pressure and suction surfaces of neighboring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid.
A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centered on the axis of a turbomachine. Pressure and suction surfaces of neighboring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row of aerofoil members includes at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan. The 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.
대표청구항
▼
1. 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, wherei
1. 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, andwherein, 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. 2. A row of aerofoil members according to claim 1, wherein the reverse compound lean results in the aerofoil member trailing edge position at midspan being circumferentially deflected, relative to the trailing edge position at the endwall, by at least 5% of the pitch between aerofoil members. 3. A row of aerofoil members according to claim 1, wherein the reverse compound lean results in the trailing edge position at midspan being circumferentially deflected, relative to the trailing edge position at the endwall, by no more than 50% of the pitch between aerofoil members. 4. A row of aerofoil members according to claim 1, wherein, in a surface swept out by rotating the tangent to the trailing edge at midspan around the axis of the turbomachine, the reverse compound lean results in an angle of inclination of at least 5° between the tangent to the trailing edge at midspan and the projection, along the direction of said axis and into said surface, of the tangent to the trailing edge at the endwall. 5. A row of aerofoil members according to claim 1, wherein, in a surface swept out by rotating the tangent to the trailing edge at midspan around the axis of the turbomachine, the reverse compound lean results in an angle of inclination of up to 40° between the tangent to the trailing edge at midspan and the projection, along the direction of said axis and into said surface, of the tangent to the trailing edge at the endwall. 6. A row of aerofoil members according to claim 1, wherein the incidence angle of the aerofoil member at the endwall and at 100% design speed of the turbomachine is within ±5° of the incidence angle of the aerofoil member at midspan and at 100% design speed. 7. A row of aerofoil members according to claim 1, wherein, r is the distance along the leading edge over which the leading edge is upstream of the leading edge at midspan, a is the distance at the endwall by which the leading edge is upstream of the leading edge at midspan, and the ratio r:a is at least 1:9. 8. A row of aerofoil members according to claim 1, wherein r is the distance along the leading edge over which the leading edge is upstream of the leading edge at midspan, a is the distance at the endwall by which the leading edge is upstream of the leading edge at midspan, and the ratio r:a is no more than 9:1. 9. A row of aerofoil members according to claim 1, wherein the ratio of the trailing edge span of the aerofoil member to its axial chord length at midspan is up to 10:1. 10. A row of aerofoil members according to claim 1, wherein the aerofoil section of the aerofoil member at the endwall has a concave pressure surface which is shaped such that three tangents can be drawn to the pressure surface at respective positions adjacent the leading edge, adjacent the trailing edge, and between the leading and trailing edges, and a fourth tangent can be drawn to the suction surface, the four tangents being parallel to each other and to the plane of the meridional section containing the leading edge at the endwall, and wherein the ratio Δ1:Δ2 is no more than 0.3, Δ1 being the circumferential spacing between the tangent to the pressure surface adjacent the leading edge and the tangent to the pressure surface between the leading and trailing edges, and Δ2 being the circumferential spacing between the tangent to the pressure surface adjacent the leading edge and the tangent to the suction surface. 11. A row of aerofoil members according to claim 1, wherein the endwall further has a region that, in meridional section, is convexly profiled immediately adjacent the suction surface and upstream of the concavely profiled region. 12. A row of aerofoil members according to claim 1, wherein the endwall has an axisymmetric cross-section upstream of the leading edge of the aerofoil member at the endwall. 13. A row of aerofoil members according to claim 1, wherein the endwall has an axisymmetric cross-section downstream of the trailing edge of the aerofoil member at the endwall. 14. A row of aerofoil members according to claim 1, which is one of a row of turbine rotor blades or row of turbine stator vanes. 15. A row of aerofoil members according to claim 1, further comprising a second radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. 16. A row of aerofoil members according to claim 15, wherein the second 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. 17. An aerofoil member for use in a circumferential row of aerofoil members that span a turbomachine annular duct centred on a rotational axis thereof, the duct for carrying a flow of compressible fluid, 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 a tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal to a radial endwall in the row,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, andwherein, 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. 18. A turbomachine comprising: an annular duct for carrying a flow of compressible fluid, the duct being centred on a rotational axis of the turbomachine; anda circumferential row of aerofoil members which span said annular duct, each of said aerofoil members 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 includes 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 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, andwherein, 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.
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