[특허]Self stowing thrust reverser

The Nordam Group, Inc.

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Self stowing thrust reverser

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-00100 F02K-00170
미국특허분류(USC)	244/110.B; 060/226.2
출원번호	US-0781410 (2004-02-18)
발명자 / 주소	Lair, Jean-Pierre
출원인 / 주소	The Nordam Group, Inc.
인용정보	피인용 횟수 : 19 인용 특허 : 20

초록

A thrust reverser includes forward and aft louvers pivotally mounted in a compartment defining a flow tunnel through the outer and inner skins of a fan nacelle. An aft flap is integrally joined to the aft louver for rotation therewith. A unison link joins together the forward and aft louvers. And, an actuator is joined to the louvers for rotation thereof between a stowed position in which the louvers and flap are closed in the nacelle skins and a deployed position in which the louvers and flap are pivoted open from the skins.

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1. A thrust reverser comprising:a fan nacelle having radially outer and inner skins extending axially from a leading edge defining an inlet to a trailing edge defining an outlet, and spaced apart radially to define a compartment spaced forwardly from said outlet; a forward louver pivotally mounted in said compartment; a forward flap pivotally mounted in said compartment below said forward louver, and pivotally joined to said forward louver for synchronization therewith; an aft louver pivotally mounted in said compartment behind said forward louver; an aft flap integrally joined to said aft louver for rotation therewith; a unison link pivotally joining together said forward and aft louvers; and an actuator joined to said louvers for rotation thereof between a stowed position contained in said compartment to a deployed position at which said forward and aft louvers are pivoted open outwardly from said outer skin, and said forward and aft flaps are pivoted open inwardly from said inner skin. 2. A reverser according to claim 1 wherein:said aft louver and aft flap are coextensive, and disposed flush with said forward flap and inner skin in said stowed position; and said forward louver is disposed flush with said outer skin in said stowed position. 3. A thrust reverser comprising:a fan nacelle having radially outer and inner skins extending axially from a leading edge defining an inlet to a trailing edge defining an outlet, and spaced apart radially to define a compartment spaced forwardly from said outlet; a forward louver pivotally mounted in said compartment, and disposed flush with said outer skin in a stowed position; an aft louver pivotally mounted in said compartment behind said forward louver, and said forward louver extends forward of said aft louver in said stowed position; an aft flat integrally joined coextensive with said aft louver for rotation therewith, and disposed flush with said inner skin in said stowed position; an aft fairing integrally joined to said aft louver, and spaced in part thereabove flush with said forward louver and outer skin in said stowed position; a unison link pivotally joining together said forward and aft louvers; and an actuator joined to said louvers for rotation thereof between said stowed position contained in said compartment to a deployed position at which said louvers are pivoted open outwardly from said outer skin, and said aft flap is pivoted open inwardly from said inner skin. 4. A reverser according to claim 3 further comprising:a forward flap pivotally mounted in said compartment below said forward louver, and disposed flush with said inner skin and aft flap in said stowed position. 5. A reverser according to claim 4 wherein said forward flap is pivotally joined to said forward louver for synchronization therewith.6. A reverser according to claim 5 wherein:said forward louver is pivotally joined near an aft end thereof in said compartment; said forward flap is pivotally joined near an aft end thereof in said compartment; and both said aft louver and aft flap are pivotally joined in common in said compartment near an aft end of said aft louver and near a forward end of said aft flap. 7. A reverser according to claim 6 further comprising:an idler link pivotally joining together said forward louver and forward flap; and a drive link pivotally joining said actuator to said forward louver for movement between said stowed and deployed positions. 8. A reverser according to claim 7 further comprising:a pair of laterally spaced apart cantilevers extending aft in said compartment; said forward louver and forward flap being pivotally joined to both said cantilevers; and a pair of said unison links pivotally joining together said forward and aft louvers at laterally opposite sides thereof. 9. A reverser according to claim 8 wherein said drive link is pivotally joined to the lateral middle of said forward louver.10. A reverser according to claim 9 wherein said idler link is pivotally joined to the lateral middle of said forward flap.11. A reverser according to claim 10 wherein said forward flap is shorter than said aft flap.12. A reverser according to claim 11 wherein forward louver is joined to said cantilevers to forwardly deploy outward, and said forward flap is joined to said cantilevers to forwardly deploy inward in counter-position with said forward louver for reverse turning exhaust flow through said nacelle.13. A reverser according to claim 12 wherein said aft louver and aft flap are pivotally joined in said compartment to parallel said forward louver in said deployed position.14. A reverser according to claim 13 further comprising:a core engine having an external core cowl mounted inside said nacelle to define an annular bypass duct therebetween terminating in a fan nozzle at said nacelle trailing edge; and said aft flap is sized to reach said core cowl when deployed, and block flow discharge through said fan nozzle for reversing thrust along said deployed louvers. 15. A fan thrust reverser comprising:a fan nacelle having outer and inner skins extending between leading and trailing edges, and an arcuate compartment between said skins having a flow tunnel extending radially therebetween; a forward louver and aft fairing pivotally mounted in said compartment to close said tunnel along said outer skin in a stowed position; a forward flap and an aft flap pivotally mounted in said compartment along said inner skin; an aft louver aligned between said forward and aft flaps in said stowed position to close said tunnel along said inner skin, and integrally joined to said aft fairing and aft flap for movement therewith; and means for deploying open in unison said forward and aft louvers and said forward and aft flaps. 16. A reverser according to claim 15 wherein:said forward louver is pivotally joined near an aft end thereof in said compartment; said forward flap is pivotally joined near an aft end thereof in said compartment; and both said aft louver and aft flap are pivotally joined in common in said compartment near an aft end of said aft louver and near a forward end of said aft flap. 17. A reverser according to claim 16 wherein:said aft louver and aft flap are coextensive, and disposed flush with said inner skin in said stowed position; and said forward louver is disposed flush with said outer skin in said stowed position. 18. A reverser according to claim 17 wherein said deploying means comprise:a unison link pivotally joining together said forward and aft louvers; an idler link pivotally joining together said forward louver and forward flap; and an actuator joined to said forward louver for rotation thereof between said stowed position and a deployed position, with said unison and idler links synchronizing rotation of said aft louver and aft flap with said forward louver and forward flap. 19. A reverser according to claim 18 wherein forward louver is joined in said compartment to forwardly deploy outward, and said forward flap is joined in said compartment to forwardly deploy inward in counter-position with said forward louver for reverse turning exhaust flow through said nacelle.20. A reverser according to claim 19 wherein said aft louver and aft flap are pivotally joined in said compartment to parallel said forward louver in said deployed position.21. A reverser according to claim 20 further comprising:a pair of laterally spaced apart cantilevers extending aft in said compartment; said forward louver and forward flap being pivotally joined to both said cantilevers; and a pair of said unison links pivotally joining together said forward and aft louvers at laterally opposite sides thereof. 22. A reverser according to claim 21 wherein said drive link is pivotally joined to the lateral middle of said forward louver.23. A reverser according to claim 22 wherein said idler link is pivotally joined to the lateral middle of said forward flap.24. A reverser according to claim 21 wherein said forward flap is shorter than said aft flap.25. A reverser according to claim 21 further comprising:a core engine having an external core cowl mounted inside said nacelle to define an annular bypass duct therebetween terminating in a fan nozzle at said nacelle trailing edge; and said aft flap is sized to reach said core cowl when deployed, and block flow discharge through said fan nozzle for reversing thrust along said deployed louvers.

이 특허에 인용된 특허 (20)

이 특허를 인용한 특허 피인용횟수: 19

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Self stowing thrust reverser

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Self stowing thrust reverser

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이 특허에 인용된 특허 (20)

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