Composite turbomachine blade
A composite turbomachine blade ( 34 ) comprises a composite material including reinforcing fibers in a matrix material, the turbomachine blade ( 34 ) comprises an aerofoil portion ( 36 ), a shank portion ( 38 ) and a root portion ( 40 ). The aerofoil portion ( 36 ) has a leading edge ( 42 ), a trailing edge ( 44 ). The composite turbomachine blade ( 34 ) also has a metallic protective member ( 52 ) arranged in the region of the leading edge ( 42 ) of the aerofoil portion ( 36 ) of the turbomachine blade ( 34 ). The metallic protective member ( 52 ) is adhesively bonded to the composite material in the region of the leading edge ( 42 ) of the aerofoil portion ( 36 ) of the composite turbomachine blade ( 34 ). The metallic protective member ( 52 ) has at least one metallic projection ( 56, 58 ) extending from the metallic protective member ( 52 ) towards the root portion ( 40 ) of the composite turbomachine blade ( 34 ). The at least one metallic projection ( 56, 58 ) reduces local peak stress levels and increases high cycle fatigue strength in the composite material, the adhesive and the metallic protective member.
1. A composite turbomachine blade comprising:
a composite material including reinforcing fibres in a matrix material, the turbomachine blade comprising:
an aerofoil portion, a shank portion and a root portion, the aerofoil portion having a tip remote from the shank portion, a leading edge, a trailing edge, a pressure surface extending from the leading edge to the trailing edge and a suction surface extending from the leading edge to the trailing edge, the composite turbomachine blade also having a protective member arranged in the region of the leading edge of the aerofoil portion of the turbomachine blade, the protective member being adhesively bonded to the composite material in the region of the leading edge of the aerofoil portion of the composite turbomachine blade, the protective member extending around the leading edge of the aerofoil portion, the protective member having portions adhesively bonded to the pressure surface and suction surface of the aerofoil portion, the protective member having an end nearest to and spaced apart from the root portion of the composite turbomachine blade, the protective member having at least one projection extending from the protective member towards the root portion of the composite turbomachine blade, the at least one projection extending from an end of the protective member nearest the root portion of the composite turbomachine blade towards the root portion of the composite turbomachine blade, the at least one projection not extending around the leading edge of the composite turbomachine blade and not extending around the trailing edge of the composite turbomachine blade, wherein the at least one projection extends onto the shank portion of the composite turbomachine blade, whereby the at least one projection reduces local peak stress levels in the composite material, the adhesive and the protective member and increases high cycle fatigue strength of the composite material, the adhesive and the protective member.
2. A composite turbomachine blade as claimed in claim 1 wherein the at least one projection extends onto the root portion of the composite turbomachine blade.
3. A composite turbomachine blade as claimed in claim 1 wherein the at least one projection tapers in thickness towards the root portion of the composite turbomachine blade.
4. A composite turbomachine blade as claimed in claim 3 wherein the at least one projection reduces in thickness gradually towards the root portion of the composite turbomachine blade.
5. A composite turbomachine blade as claimed in claim 1 wherein the protective member having two projections, a first one of the projections being arranged on the pressure surface of the aerofoil portion of the composite turbomachine blade and a second one of the projections being arranged on the suction surface of the aerofoil portion of the composite turbomachine blade.
6. A composite turbomachine blade as claimed in claim 1 wherein the reinforcing fibres comprise carbon fibres and/or glass fibres.
7. A composite turbomachine blade as claimed in claim 1 wherein the matrix material comprises a thermosetting resin.
8. A composite turbomachine blade as claimed in claim 1 wherein the composite turbomachine blade is composite gas turbine engine blade.
9. A composite turbomachine blade as claimed in claim 1 wherein the composite turbomachine blade is a fan blade.
10. A composite turbomachine blade as claimed in claim 1 wherein the protective member is a metallic protective member and the at least one projection is a metallic projection.
11. A composite turbomachine blade as claimed in claim 1 wherein the protective member extends the full length of the aerofoil portion from the tip to the shank portion.
12. A composite turbomachine blade as claimed in claim 1 wherein the protective member does not extend over a leading edge of the majority of the shank portion.
13. A composite turbomachine blade as claimed in claim 1 wherein the at least one projection is flexible.
14. A composite turbomachine blade as claimed in claim 1 wherein the at least one projection is arranged on the pressure surface of the aerofoil portion of the composite turbomachine blade.
15. A composite turbomachine blade as claimed in claim 1 wherein the at least one projection is arranged on the suction surface of the aerofoil portion of the composite turbomachine blade.
16. A composite turbomachine blade comprising:
a composite material including reinforcing fibres in a matrix material, the turbomachine blade comprising:
an aerofoil portion, a shank portion and a root portion, the aerofoil portion having a tip remote from the shank portion, a leading edge, a trailing edge, a pressure surface extending from the leading edge to the trailing edge and a suction surface extending from the leading edge to the trailing edge, the composite turbomachine blade also having a protective member arranged in the region of the leading edge of the aerofoil portion of the turbomachine blade, the protective member extends the full length of the aerofoil portion from the tip to the shank portion, the protective member being adhesively bonded to the composite material in the region of the leading edge of the aerofoil portion of the composite turbomachine blade, the protective member extending around the leading edge of the aerofoil portion, the protective member having portions adhesively bonded to the pressure surface and suction surface of the aerofoil portion, the protective member having an end nearest to and spaced apart from the root portion of the composite turbomachine blade, the protective member having at least one projection extending from the protective member towards the root portion of the composite turbomachine blade, the at least one projection extending from an end of the protective member nearest the root portion of the composite turbomachine blade towards the root portion of the composite turbomachine blade, the at least one projection extending onto the shank portion of the composite turbomachine blade, the at least one projection not extending around the leading edge of the composite turbomachine blade, the at least one projection being arranged to reduce local peak stress levels in the composite material, the adhesive and the protective member and to increase high cycle fatigue strength of the composite material, the adhesive and the protective member.
17. A turbomachine rotor assembly comprising a turbomachine rotor and a plurality of circumferentially spaced radially extending composite turbomachine blades as claimed in claim 1 .
18. A composite turbomachine blade comprising:
a composite material including reinforcing fibres in a matrix material, the turbomachine blade comprising:
an aerofoil portion, a shank portion and a root portion, the aerofoil portion having a tip remote from the shank portion, a leading edge, a trailing edge, a pressure surface extending from the leading edge to the trailing edge and a suction surface extending from the leading edge to the trailing edge, the composite turbomachine blade also having a protective member arranged in the region of the leading edge of the aerofoil portion of the turbomachine blade, the protective member being adhesively bonded to the composite material in the region of the leading edge of the aerofoil portion of the composite turbomachine blade, the protective member extending around the leading edge of the aerofoil portion, the protective member having portions adhesively bonded to the pressure surface and suction surface of the aerofoil portion, the protective member having an end nearest to and spaced apart from the root portion of the composite turbomachine blade, the protective member having at least one projection extending from the protective member towards the root portion of the composite turbomachine blade, the at least one projection extending from an end of the protective member nearest the root portion of the composite turbomachine blade towards the root portion of the composite turbomachine blade, the at least one projection being spaced from the leading edge, wherein the at least one projection extends onto the shank portion of the composite turbomachine blade, whereby the at least one projection reduces local peak stress levels in the composite material, the adhesive and the protective member and increases high cycle fatigue strength of the composite material, the adhesive and the protective member.