초록 ▼

A composite blade (26) comprises a root portion (36) and an aerofoil portion (38). The aerofoil portion (38) has a tip (42), a chord (C), a leading edge (44), a trailing edge (46), a suction surface (48) extending from the leading edge (44) to the trailing edge (46) and a pressure surface extending

A composite blade (26) comprises a root portion (36) and an aerofoil portion (38). The aerofoil portion (38) has a tip (42), a chord (C), a leading edge (44), a trailing edge (46), a suction surface (48) extending from the leading edge (44) to the trailing edge (46) and a pressure surface extending from the leading edge (44) to the trailing edge (46). The composite blade (26) comprises reinforcing fibres (52) in a matrix material (54). The aerofoil portion (38) adjacent the root portion (36) has regions (56, 58) at least at the leading edge (44) and trailing edge (46) comprising an asymmetric lay up of reinforcing fibres (52) and the aerofoil portion (38) adjacent the tip (42) having at least a region (62) at the mid-chord comprising an asymmetric lay up of reinforcing fibres (52).

대표청구항 ▼

The invention is claimed is: 1. A composite blade comprising a root portion and an aerofoil portion, the aerofoil portion having a tip, a chord, a leading edge, a trailing edge, a suction surface extending from the leading edge to the trailing edge and a pressure surface extending from the leading

The invention is claimed is: 1. A composite blade comprising a root portion and an aerofoil portion, the aerofoil portion having a tip, a chord, a leading edge, a trailing edge, a suction surface extending from the leading edge to the trailing edge and a pressure surface extending from the leading edge to the trailing edge, the composite blade comprising reinforcing fibres in a matrix material, the aerofoil portion adjacent the tip having at least a region at the mid chord comprising an asymmetric arrangement of reinforcing fibres, said asymmetric arrangement of reinforcing fibers subjected to in plane loads during operation, said in plane loads causing said aerofoil to bend at said mid chord region adjacent said tip of said blade which in turn causes said tip of said blade to bend between a C-shaped formed cross-section and an S-shaped formed cross-section. 2. A composite blade as claimed in claim 1 wherein the aerofoil portion adjacent the root portion having regions at least at the leading edge and trailing edge comprising an asymmetric arrangement of reinforcing fibres, said composite blade being movable between a first position having a first twist angle and a second position having a second twist angle. 3. A composite blade as claimed in claim 1 wherein the composite blade is any one of a compressor blade, a fan blade, a propeller blade or a turbine blade. 4. A composite blade as claimed in claim 3 wherein the composite blade comprises a metal matrix material. 5. A composite blade as claimed in claim 4 wherein the composite blade comprises ceramic fibres. 6. A composite blade as claimed in claim 5 wherein the ceramic fibres comprise silicon carbide fibres or silicon nitride fibres. 7. A composite blade as claimed in claim 3 wherein the composite blade comprises a ceramic matrix material. 8. A composite blade as claimed in claim 1 wherein the composite blade comprises an organic matrix material. 9. A composite blade as claimed in claim 8 wherein the organic matrix material comprises an epoxy resin. 10. A composite blade as claimed in claim 8 wherein the reinforcing fibres comprise carbon fibres or glass fibres. 11. A composite blade as claimed in claim 1 wherein the asymmetric arrangement of reinforcing fibres comprising an asymmetric lay up of layers of reinforcing fibres. 12. A composite blade as claimed in claim 1 wherein the asymmetric arrangement of reinforcing fibres comprising an asymmetric arrangement of three dimensionally woven reinforcing fibres. 13. A composite blade comprising a root portion and an aerofoil portion, the aerofoil portion having a tip, a chord, a leading edge, a trailing edge, a suction surface extending from the leading edge to the trailing edge and a pressure surface extending from the leading edge to the trailing edge, the composite blade comprising reinforcing fibres in a matrix material, the aerofoil portion adjacent the tip having at least a region at the mid chord comprising an asymmetric arrangement of reinforcing fibres wherein an active control mechanism is provided in the aerofoil portion. 14. A composite blade as claimed in claim 13 wherein the active control mechanism comprising a shape memory material member. 15. A composite blade as claimed in claim 13 wherein the active control mechanism comprising a piezoelectric member. 16. A rotor assembly comprising a rotor carrying a plurality of circumferentially arranged radially outwardly extending composite blades, each composite blade comprising a root portion and an aerofoil portion, the aerofoil portion having a tip, a chord, a leading edge, a trailing edge, a suction surface extending from the leading edge to the trailing edge and a pressure surface extending from the leading edge to the trailing edge, each composite blade comprising reinforcing fibres in a matrix material, the aerofoil portion adjacent the tip having at least a region at the mid chord comprising an asymmetric arrangement of reinforcing fibres such that in operation the tip of the composite blade is movable between a first position having a C-shaped cross-section at a first rotational speed and a second position having an S-shaped cross-section at a second, higher, rotational speed. 17. A rotor assembly as claimed in claim 16 wherein the aerofoil portion adjacent the root portion having regions at least at the leading edge and trailing edge comprising an asymmetric arrangement of reinforcing fibres such that in operation the composite blade is movable between a first position having a first twist angle at the first rotational speed and a second position having a second, smaller, twist angle at the second, higher, rotational speed. 18. A rotor assembly as claimed in claim 17 wherein each composite blade having an active control mechanism to move the composite blade between the first twist angle and the second twist angle. 19. A rotor assembly as claimed in claim 16 wherein the composite blades are compressor blades, fan blades, propeller blades or turbine blades. 20. A rotor assembly as claimed in claim 16 wherein the composite blades comprise an organic matrix material. 21. A rotor assembly as claimed in claim 20 wherein the organic matrix material comprises an epoxy resin. 22. A rotor assembly as claimed in claim 20 wherein the reinforcing fibres comprise carbon fibres or glass fibres. 23. A rotor assembly as claimed in claim 16, wherein the composite blades comprise a metal matrix material. 24. A rotor assembly as claimed in claim 23 wherein the composite blade comprises ceramic fibres. 25. A rotor assembly as claimed in claim 24 wherein the ceramic fibres comprise silicon carbide fibres or silicon nitride fibres. 26. A rotor assembly as claimed in claim 16, wherein the composite blades comprise a ceramic matrix material. 27. A rotor assembly as claimed in claim 16 wherein the asymmetric arrangement of reinforcing fibres comprises an asymmetric lay up of layers of reinforcing fibres. 28. A rotor assembly as claimed in claim 16 wherein the asymmetric arrangement of reinforcing fibres comprises an asymmetric arrangement of three dimensionally woven reinforcing fibres. 29. A rotor assembly as claimed in claim 16 wherein each composite blade having an active control mechanism to move the tip of the aerofoil position between the first position having a C-shaped cross-section and the second position having an S-shaped cross-section.