[특허]Composite annular seal assembly for bearings in aircraft

Roller Bearing Company of America, Inc.

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특허 상세정보

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Composite annular seal assembly for bearings in aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-009/02 F16C-033/78 F16C-023/08 F16C-033/36
출원번호	US-0294947 (2014-06-03)
등록번호	US-9227720 (2016-01-05)
발명자 / 주소	Habibvand, Alex
출원인 / 주소	Roller Bearing Company of America, Inc.
대리인 / 주소	MKG, LLC
인용정보	피인용 횟수 : 4 인용 특허 : 17

초록
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An edge flap arrangement is provided for an aircraft wing and includes a main flap element and an actuator for moving the main flap element relative to the wing. A linkage arrangement supports the main flap element from the aircraft wing for movement relative to the wing, and includes including a drop hinge link arrangement having a fixed strut secured to the aircraft wing and a drop link secured to the main flap element. The fixed strut and drop link are pivotally connected by a hinge point having a bearing installed therein. The bearing includes an out...

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1. An edge flap arrangement for an aircraft wing, the arrangement comprising: a main flap element and an actuator for moving the main flap element relative to the aircraft wing;a linkage arrangement supporting the main flap element from the aircraft wing for movement relative to the aircraft wing, the linkage arrangement including a drop hinge link arrangement, the drop hinge link arrangement including a fixed strut secured to the aircraft wing and a drop link secured to the main flap element, the fixed strut and the drop link being pivotally connected by a hinge point;the hinge point comprising at least a first bearing, the first bearing comprising: an outer race having a first inner surface and an interior area, a radially inward facing groove adjacent to the first inner surface; an inner race having an outer surface, a portion of the inner race being disposed in the interior area;an annular seal assembly being circumferentially continuous and laterally deflectable and thereby snap-fit into the groove, the annular seal assembly being configured to withstand relative misalignment between the inner race and the outer race, the annular seal assembly comprising:a first annular retaining ring defining a first radially outermost portion;a second annular retaining ring defining a second radially outermost portion; anda resilient ring defining a third radially outermost portion, the resilient ring being disposed between the first annular retaining ring and the second annular retaining ring;the first radially outermost portion, the second radially outermost portion and the third radially outermost portion being aligned with one another;the resilient ring projecting radially inward from the first annular retaining ring and the second annular retaining ring; andthe resilient ring being more compressible and flexible than the first annular retaining ring and the second annular retaining ring. 2. The edge flap arrangement of claim 1, further comprising: at least a second bearing installed in the actuator for moving the main flap element relative to the aircraft wing, the at least one second bearing comprising:an outer race having a first inner surface and an interior area;an inner race having an outer surface, a portion of the inner race being disposed in the interior area;an annular seal assembly snap-fit into the outer race, the annular seal assembly comprising:a first annular retaining ring defining a first radially outermost portion;a second annular retaining ring defining a second radially outermost portion; anda resilient ring defining a third radially outermost portion, the resilient ring being disposed between the first annular retaining ring and the second annular retaining ring;the first radially outermost portion, the second radially outermost portion and the third radially outermost portion being aligned with one another;the resilient ring projecting radially inward from the first annular retaining ring and the second annular retaining ring; andthe resilient ring being more compressible and flexible than the first annular retaining ring and the second annular retaining ring. 3. The edge flap arrangement of claim 1 wherein the hinge point comprises a plurality of first bearings. 4. The edge flap arrangement of claim 2 wherein the actuator comprises a plurality of second bearings. 5. The edge flap arrangement of claim 1 wherein the edge flap is for a trailing edge of a wing of an aircraft. 6. The edge flap arrangement of claim 1 wherein the aircraft has two engines, up to 7,950 nautical mile flying range, up to a 64.7 meter wingspan and employs at least 50 percent of composites in the fuselage and wing. 7. The edge flap arrangement of claim 1, the first bearing further comprising: a plurality of first hourglass rollers, each of the plurality of first hourglass rollers having a generally concave outer surface, the plurality of first hourglass rollers being disposed between the inner race and the outer race;the first inner surface being convex and the outer surface being convex; andeach of the plurality of first hourglass rollers engaging the outer surface and the first inner surface. 8. The edge flap arrangement of claim 7, the first bearing further comprising: a second inner surface defined by the outer race, the second inner surface being convex;a plurality of second hourglass rollers, each of the plurality of second hourglass rollers having a generally concave outer surface, the plurality of second hourglass rollers being disposed between the inner race and the outer race; andeach of the plurality of second hourglass rollers engaging the outer surface and the second inner surface. 9. The edge flap arrangement of claim 2, the second bearing further comprising: a plurality of first hourglass rollers, each of the plurality of first hourglass rollers having a generally concave outer surface, the plurality of first hourglass rollers being disposed between the inner race and the outer race;the first inner surface being convex and the outer surface being convex; andeach of the plurality of first hourglass rollers engaging the outer surface and the first inner surface. 10. The edge flap arrangement of claim 9, the second bearing further comprising: a second inner surface defined by the outer race, the second inner surface being convex;a plurality of second hourglass rollers, each of the plurality of second hourglass rollers having a generally concave outer surface, the plurality of second hourglass rollers being disposed between the inner race and the outer race; andeach of the plurality of second hourglass rollers engaging the outer surface and the second inner surface. 11. A bearing installed in a wing flap actuator of an aircraft, the bearing comprising: an outer race having a first inner surface and an interior area, a radially inward facing groove adjacent to the first inner surface;an inner race having an outer surface, a portion of the inner race being disposed in the interior area;an annular seal assembly being circumferentially continuous and laterally deflectable and thereby snap-fit into the groove, the annular seal assembly being configured to withstand relative misalignment between the inner race and the outer race, the annular seal assembly comprising:a first annular retaining ring defining a first radially outermost portion;a second annular retaining ring defining a second radially outermost portion; anda resilient ring defining a third radially outermost portion, the resilient ring being disposed between the first annular retaining ring and the second annular retaining ring;the first radially outermost portion, the second radially outermost portion and the third radially outermost portion being aligned with one another;the resilient ring projecting radially inward from the first annular retaining ring and the second annular retaining ring; andthe resilient ring being more compressible and flexible than the first annular retaining ring and the second annular retaining ring. 12. The bearing according to claim 11 wherein the wing flap is for a trailing edge of a wing of an aircraft. 13. The edge flap arrangement of claim 1, wherein the groove defines a lip axially outward therefrom, the lip having an inside diameter and the annular seal assembly defines an outside diameter and the outside diameter is of a magnitude less than the inside diameter sufficient to allow the lateral deflectability of the annular seal assembly. 14. The edge flap arrangement of claim 11, wherein the groove defines a lip axially outward therefrom, the lip having an inside diameter and the annular seal assembly defines an outside diameter and the outside diameter is of a magnitude less than the inside diameter sufficient to allow the lateral deflectability of the annular seal assembly.

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이 특허를 인용한 특허 피인용횟수: 4

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Composite annular seal assembly for bearings in aircraft

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이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 4

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Composite annular seal assembly for bearings in aircraft

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이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 4

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IPC 상세정보(version : 201201)

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