[특허]System and method for reducing rotor blade noise

Bell Helicopter Textron Inc.

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System and method for reducing rotor blade noise

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-007/00 B64C-023/06 B64C-027/467 B64C-027/615 B64C-027/72 F01D-005/14
출원번호	US-0785892 (2013-03-05)
등록번호	US-9464532 (2016-10-11)
발명자 / 주소	Sutton, Drew
출원인 / 주소	Bell Helicopter Textron Inc.
대리인 / 주소	Fish & Richardson P.C.
인용정보	피인용 횟수 : 1 인용 특허 : 15

초록

A rotor blade includes an active flap and an airflow disturber configured to selectively alter airflow across the active flap.

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1. A rotor blade, comprising: an active flap; andan airflow disturber disposed at least partially on the active flap and selectively extending from a surface profile of the active flap, the airflow disturber comprising a wedge disturber having a triangular profile, wherein a point of the triangular profile points toward a leading edge of the rotor blade, the airflow disturber configured to selectively alter airflow across the active flap; andwherein the airflow disturber is selectively extendible between a first stowed position that does not extend beyond the surface profile of the active flap, a second deployed position of the airflow disturber that extends beyond the surface profile of the active flap, and a third partially deployed position of the active flap between the first stowed position and the second deployed position. 2. The rotor blade of claim 1, wherein airflow disturber is deployable without deploying the active flap. 3. The rotor blade of claim 1, comprising a plurality of wedge disturbers each having a triangular profile, wherein a point of each triangular profile points toward a leading edge of the rotor blade; and wherein the plurality of wedge disturbers comprises the first-mentioned wedge disturber disposed on the rotor blade, a second wedge disturber disposed on the rotor blade, and a third wedge disturber disposed on the active flap of the rotor blade. 4. The rotor blade of claim 3, wherein the third wedge disturber is disposed longitudinally between the first wedge disturber and the second wedge disturber with respect to a longitudinal axis of the rotor blade. 5. A rotor system, comprising: a first rotor blade comprising an active flap configured to move relative to an adjacent surface profile of the first rotor blade, wherein a gap exists between the active flap and the adjacent surface profile of the first rotor blade;a flap shield comprising a first end attached to the first rotor blade and a second end opposite the first end attached to the active flap, wherein, in response to the active flap moving relative to the surface profile of the first rotor blade, the flap shield is configured to deform between the first rotor blade and the active flap to close the gap between the active flap and the adjacent surface profile of the first rotor blade; anda plurality of airflow disturbers disposed on the first rotor blade and configured to selectively disturb airflow across the active flap of the first rotor blade, the plurality of airflow disturbers comprising a first wedge disturber having a triangular profile, wherein a point of the triangular profile points toward a leading edge of the first rotor blade. 6. The rotor system of claim 5, further comprising a second rotor blade comprising a second active flap, wherein the plurality of airflow disturbers is configured to selectively disturb airflow such that airflow across the first rotor blade is different than airflow across the second rotor blade. 7. The rotor system of claim 5, wherein the plurality of airflow disturbers comprises a gate disturber. 8. The rotor system of claim 5, wherein the plurality of airflow disturbers is disposed at least partially on the first rotor blade and not on the associated active flap of the first rotor blade. 9. The rotor system of claim 5, wherein the plurality of airflow disturbers is disposed at least partially on the associated active flap of the first rotor blade and not on a remainder of the first rotor blade. 10. The rotor system of claim 5, wherein the plurality of airflow disturbers is disposed at least partially on the first rotor blade and on the associated active flap of the first rotor blade. 11. The rotor system of claim 5, wherein the flap shield comprises a plurality of pivotable stacked elements configured to pivot in unison with the active flap. 12. The rotor system of claim 5, wherein the flap shield comprises a folded sheet of material. 13. The rotor system of claim 5, wherein the flap shield comprises a selectively rolled sheet of material, and the rotor blade comprises a receptacle in an interior of the rotor blade, the selectively rolled sheet of material of the flap shield configured to roll into or out of the receptacle to close the gap between the active flap and the rotor blade. 14. The rotor system of claim 5, wherein the plurality of airflow disturbers comprises the first wedge disturber disposed on the first rotor blade and not on the associated active flap of the first rotor blade, a second wedge disturber disposed on the first rotor blade and not on the associated active flap of the first rotor blade, and a third wedge disturber disposed on the active flap of the first rotor blade, wherein the second wedge disturber and the third wedge disturber each comprise a triangular profile, wherein a point of each of the triangular profiles points toward the leading edge of the rotor blade. 15. The rotor system of claim 14, wherein the third wedge disturber is disposed longitudinally between the first wedge disturber and the second wedge disturber with respect to a longitudinal axis of the first rotor blade. 16. A method comprising: attaching a flap shield in a gap between an active flap of a rotor blade and an adjacent surface profile of the rotor blade, wherein the flap shield comprises a first end attached to the rotor blade and a second end opposite the first end attached to the active flap;moving the active flap of the rotor blade relative to the adjacent surface profile of the rotor blade between an inactive position of the active flap within the adjacent surface profile of the rotor blade and a deployed position of the active flap offset from the adjacent surface profile of the rotor blade;deforming, in response to moving the active flap of the rotor blade, the flap shield between the rotor blade and the active flap to close the gap between the active flap and the adjacent surface profile of the rotor blade, andselectively extending an airflow disturber disposed on the rotor blade beyond the surface profile of the rotor blade to interact with airflow over the rotor blade, the airflow disturber comprising a wedge disturber having a triangular profile, wherein a point of the triangular profile points toward a leading edge of the rotor blade. 17. The method of claim 16, further comprising selectively extending second airflow disturber disposed on the active flap of the rotor blade beyond a surface profile of the active flap to interact with airflow over the active flap, the second airflow disturber comprising a second wedge disturber having a triangular profile, wherein a point of the triangular profile points toward the leading edge of the rotor blade.

이 특허에 인용된 특허 (15)

이 특허를 인용한 특허 피인용횟수: 1

Hutcheson, Florence V.; Brooks, Thomas F.. Flow disruption devices for the reduction of high lift system noise. USP20190410252792.

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System and method for reducing rotor blade noise

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System and method for reducing rotor blade noise

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이 특허에 인용된 특허 (15)

이 특허를 인용한 특허 피인용횟수: 1

IPC 상위 출원인

상세정보조회

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IPC 상세정보(version : 201201)

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