Blade with adaptive twisting, and a rotor provided with such a blade
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/473
B64C-027/59
B64C-027/33
F03D-001/06
B64C-027/54
B29L-031/08
출원번호
US-0033213
(2011-02-23)
등록번호
US-8821128
(2014-09-02)
우선권정보
FR-10 00809 (2010-02-26)
발명자
/ 주소
Bianchi, Laurent
Cuenca, Rémy
Galan, Mathieu
Reveillon, Damien
출원인 / 주소
Airbus Helicopters
대리인 / 주소
Brooks Kushman P.C.
인용정보
피인용 횟수 :
2인용 특허 :
9
초록▼
A rotor blade (1) with adaptive twisting, the blade being provided with an outer covering (2) extending along a pitch variation axis (AY) from a first end zone (3) to a second end zone (4), the outer covering (2) defining an internal cavity (8). The blade includes a strip (10) extending inside said
A rotor blade (1) with adaptive twisting, the blade being provided with an outer covering (2) extending along a pitch variation axis (AY) from a first end zone (3) to a second end zone (4), the outer covering (2) defining an internal cavity (8). The blade includes a strip (10) extending inside said cavity (8) along said pitch variation axis (AY), said strip (10) comprising a composite material that is anisotropic so as to be suitable for twisting under the effect of centrifugal forces (F) directed parallel to said pitch variation axis (AY) when the blade (1) is in rotation, said strip (10) being fastened to said outer covering (2) via first and second fastener means (11, 12) in order to be capable of twisting said outer covering (2).
대표청구항▼
1. A rotor blade with adaptive twisting, the blade being provided with an outer covering extending along a pitch variation axis from a first end zone to a second end zone, the outer covering defining an internal cavity, the blade including a strip extending inside said cavity, said strip comprising
1. A rotor blade with adaptive twisting, the blade being provided with an outer covering extending along a pitch variation axis from a first end zone to a second end zone, the outer covering defining an internal cavity, the blade including a strip extending inside said cavity, said strip comprising a composite material that is anisotropic and that is twisting under the effect of centrifugal forces when the blade is in rotation, said strip being fastened to said outer covering by first fastener means and second fastener means that twist as the strip is twisting thereby twisting said outer covering. 2. A blade according to claim 1, said strip comprising a stack of unidirectional composite plies that are antisymmetrical about a middle ply. 3. A blade according to claim 2, said middle ply having a plurality of reference fibers extending in a reference direction, a first ply and a second ply of the stack being disposed symmetrically on either side of said middle ply, said first ply being arranged between said middle ply and a suction side skin of said outer covering and presenting first fibers at a first angle relative to said reference direction, said second ply being arranged between said middle ply and a pressure side skin of said outer covering and presenting second fibers having a second angle relative to said reference direction, said first angle being equal and opposite to said second angle. 4. A blade according to claim 2, said middle ply having a plurality of reference fibers extending in a reference direction, which reference direction is parallel to said pitch variation axis. 5. A blade according to claim 2, said stack having varying numbers of plies along the span of said blade. 6. A blade according to claim 1, an end of said strip projecting from said first end zone of said covering to represent a first end of the blade suitable for fastening to a hub. 7. A blade according to claim 1, said first fastener means being spaced apart from said second fastener means on the strip by an offset along a chord of the blade such that the first and second fastener means are connected to opposed ends of the strip, wherein the first and second fastener means are independent of overlap across the strip. 8. A blade according to claim 1, said first fastener means extending in the cavity along a first longitudinal direction parallel to said pitch variation axis, and the second fastener means extending in the cavity along a second longitudinal direction parallel to said pitch variation axis. 9. A blade according to claim 1, said outer covering comprising a pressure side skin and a suction side skin, said strip comprising an intermediate zone positioned between a front zone close to a leading edge of the blade and a rear zone close to a trailing edge of the blade, said first fastener means fastening the front zone to one of said skins, and the second fastener means fastening the rear zone to the other skin to which the front zone is not fastened, wherein the first and second fastener means are spaced apart from one another by the intermediate zone. 10. A blade according to claim 1, including a leading edge spar connecting a pressure side skin to a suction side skin of said outer covering. 11. A blade according to claim 1, including a trailing edge ledge positioned between and connecting a pressure side skin to a suction side skin of said outer covering. 12. A blade according to claim 1, said outer covering comprising a pressure side skin and a suction side skin, and at least one of the skins comprising a composite material that is anisotropic. 13. A blade according to claim 1, at least one segment of said blade having the first and second fastener means being twisted, said at least one segment of said blade presenting a twist relationship. 14. A rotorcraft rotor having a hub and a plurality of blades, at least one blade being according to claim 1. 15. The rotorcraft blade according to claim 1 wherein the strip lies along and is parallel with a chord of the blade. 16. A rotor blade with adaptive twisting, the blade comprising: an outer covering extending along a pitch variation axis from a first end zone to a second end zone, the outer covering defining an internal cavity;an anisotropic composite strip extending inside said cavity and comprising a stack of unidirectional fibers oriented in a first direction, a first ply of unidirectional fibers oriented in a second direction and a second ply of unidirectional fibers oriented in a third direction; andfirst and second fasteners connecting opposed ends of the strip to the outer covering, each fastener extending between the outer covering and a respective end of the strip;wherein the strip is adapted to twist in response to centrifugal forces caused by rotation of the blade; andwherein the first and second fasteners are configured to twist in response to the strip twisting thereby causing the outer covering to twist. 17. The rotor blade of claim 16 wherein the first ply is adjacent to the second ply; and wherein the first direction is parallel to the pitch variation axis. 18. A rotorcraft blade comprising: an outer covering extending along a pitch variation axis from a first end zone to a second end zone, the outer covering defining an internal cavity;a spar provided by an anisotropic composite strip extending inside said cavity and having a first end and a second end, the first end adjacent to the first end zone of the outer covering, the second end projecting beyond the second end zone of the outer covering and adapted to connect to a hub of a rotorcraft, the anisotropic composite strip comprising a stack of unidirectional fibers oriented to be parallel to the twist variation axis, a first ply of unidirectional fibers oriented in a first direction, and a second ply of unidirectional fibers oriented in a second direction, wherein the stack, the first ply, and the second ply extend from the first end to the second end of the strip, wherein twist of the strip is a function of a speed of rotation of the strip such that the strip twists along the pitch variation axis in response to centrifugal forces imposed on the strip when the blade is in rotation to provide active twist; andfirst and second fasteners connecting the strip to the outer covering, the first and second fasteners configured to twist in response to the strip twisting to twist the outer covering. 19. The rotorcraft blade of claim 18 wherein each of the first and second fasteners comprise an open channel extending between the first and second ends of the strip; wherein the first fastener is positioned adjacent to the leading edge of the blade, and the second fastener is positioned adjacent to the trailing edge of the blade; andwherein a rear edge of the first fastener is spaced apart from a front edge of the second fastener by an offset along a chord of the blade such that the first fastener is independent of an overlap with the second fastener. 20. The rotorcraft blade of claim 18 wherein each of the first and second fasteners comprise a plurality of U-shaped section members distributed longitudinally between the first and second ends of the strip.
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이 특허에 인용된 특허 (9)
Hunt James (King County WA), Aerodynamic structures of composite construction.
Bost Michel (Joinville-le-Pont FRX), Composite material blade with twin longeron and twin box structure having laminated honeycomb sandwich coverings and a m.
Zamponi, Laurent; Fontaine, Nicolas; Durand, Valerian; Hirsch, Jean-Francois; Grohmann, Boris, Adaptively-twistable blade, and an aircraft including such a blade.
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