[특허]Translating variable area fan nozzle providing an upstream bypass flow exit

[미국특허] Translating variable area fan nozzle providing an upstream bypass flow exit 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-001/09 F02K-003/075 F02K-001/70
출원번호	US-0485551 (2009-06-16)
등록번호	US-8402765 (2013-03-26)
발명자 / 주소	Amkraut, Daniel M. Layland, Michael John James, Norman John
출원인 / 주소	Rohr, Inc.
대리인 / 주소	Womble Carlyle Sandridge & Rice, LLP
인용정보	피인용 횟수 : 9 인용 특허 : 42

초록 ▼

A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.

대표청구항 ▼

1. A nacelle assembly for a turbofan aircraft engine having a centerline, the nacelle comprising: (a) a forward nacelle portion having an outer fairing and a trailing edge;(b) a translatable variable area fan nozzle comprising at least one nozzle segment, the nozzle segment having a leading edge and a first end and being selectively movable between a stowed position and one or more deployed positions, wherein in the deployed positions, an upstream bypass flow exit is formed between the trailing edge and the leading edge and in at least the stowed position, the nozzle segment overlaps with the forward nacelle trailing edge;(c) a split beavertail fairing comprising an upstream fairing portion on the outer fairing of the forward nacelle portion and a downstream fairing portion on the first end of at least one nozzle segment, wherein when the nozzle segment is in the stowed position, the upstream fairing portion and the downstream fairing portion combine to form a substantially continuous outer surface extending between the forward nacelle portion and the at least one nozzle segment; and(d) a deflector located proximate to the first end of the at least one nozzle segment and adjacent the split beavertail fairing, wherein the deflector is configured to substantially block air flow that exits the nacelle assembly through the upstream bypass flow exit from contacting the split beavertail fairing when the nozzle segment is in the deployed position;wherein the deflector is affixed to the nacelle and rearwardly extends from the trailing edge;wherein at least a portion of the deflector overlaps a portion of the nozzle segment when the nozzle segment is in a fully deployed position of said one or more deployed positions. 2. A nacelle assembly according to claim 1 wherein the forward nacelle portion is a stationary forward cowl. 3. A nacelle assembly according to claim 1 wherein the forward nacelle portion is a translatable thrust reverser sleeve. 4. A nacelle assembly according to claim 1 wherein a gap is formed between the upstream fairing portion and the downstream fairing portion when the nozzle segment is in the one or more deployed positions, and wherein the deflector is configured to substantially block air flow that exits the nacelle assembly through the upstream bypass flow exit from passing through the gap when the nozzle segment is in the one or more deployed positions. 5. A variable area fan nozzle assembly for a turbofan engine assembly having a primary bypass flow exit for discharging engine bypass flow, the assembly comprising: (a) a forward nacelle portion having a trailing edge;(b) a translating nozzle segment having a leading edge and a first end;(c) support means for movably supporting the first end of the translating nozzle segment such that the nozzle segment is movable between a stowed position and a deployed position, wherein an upstream bypass flow exit is formed between the leading edge and the trailing edge when the nozzle segment is in the deployed position and in at least the stowed position, the nozzle segment overlaps with the forward nacelle trailing edge;(d) a fairing at least partially covering the support means; and(e) means for substantially preventing air from passing through the upstream bypass flow exit in a region proximate to the fairing;wherein the means for substantially preventing air from passing through the upstream bypass flow exit proximate to the fairing comprises a deflector adjacent to the fairing and attached to the forward nacelle portion and rearwardly extending from the trailing edge;wherein at least a portion of the deflector overlaps a portion of the nozzle segment when the nozzle segment is in the fully deployed position.

이 특허에 인용된 특허 (42) 인용/피인용 타임라인 분석

Davies Stephen Harlow,GBX, Actuator.
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Timms Richard H. (San Diego County CA), Aircraft thrust reverser mechanism.
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Lair, Jean-Pierre; Peters, Frederick Henry, Bifold door thrust reverser.
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Remlaoui Jihad I. (Oceanside CA), Cascade type aircraft engine thrust reverser with hidden link actuator.
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Ramlaoui, Jihad I.; Seaver, Randall J.; James, Norman J.; Byrne, Stuart J.; Cornejo, Sheila, Cascadeless fan thrust reverser with plume control.
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Nikkanen John P. (West Hartford CT), Compact thrust reverser.
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Lair, Jean-Pierre, Confluent exhaust nozzle.
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Lair, Jean-Pierre, Confluent variable exhaust nozzle.
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Carimali Flix (Le Havre FRX) Legras Michel J. L. (Le Havre FRX), Deflector edge for a thrust reverser.
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Baudu Pierre Andre Marcel,FRX ; Gonidec Patrick,FRX ; Vauchel Guy Bernard,FRX, Electric control system for a turbojet engine thrust reverser including an electromechanical drive device and a locking.
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Lair,Jean Pierre; Wolters,Gregory Thomas, Induction coupled variable nozzle.
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Bulin, Guillaume; Oberle, Patrick; Surply, Thierry, Jet engine nacelle for an aircraft and aircraft comprising such a nacelle.
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Davies,Stephen Harlow; Guy,Mark Anthony; Somerfield,Michael Paul; Tucker,David Roy, Linear actuator.
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Davies Stephen H. (Telford GB2), Lock for an engine thrust reverser.
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Davies Stephen H. (Telford GB2), Lock for an engine thrust reverser.
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Lymons, Dennis E.; Terrey, Colin R., Lock for the translating sleeve of a turbofan engine thrust reverser.
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Dehu,Michel Philippe; Lore,Xavier Raymond Yves, Locking system on a cascade thrust reverser.
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Lair,Jean Pierre, Nested latch thrust reverser.
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Dubois Claude A. G. (Honfleur FRX), Pivoting door cascade thrust reverser.
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Lair, Jean-Pierre, Recessed engine nacelle.
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Lair, Jean-Pierre, Rotary adjustable exhaust nozzle.
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Jean Michel Christian Marie,FRX, Self-closing pivoting door thrust reverser.
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Lair,Jean Pierre, Spider actuated thrust reverser.
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Richard G Stretton GB, Thrust reverser.
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Timms Richard H. (San Diego CA), Thrust reverser geared linkage.
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Lair Jean-Pierre (8023 Vantage ; Suite 1450 San Antonio TX 78230), Thrust reverser integrating a variable exhaust area nozzle.
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Johnson, Andrew T., Thrust reverser position determination system and method.
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Smith, Craig M., Thrust reverser with sliding pivot joints.
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Butler Lawrence (Cincinnati OH), Thrust reverser with variable nozzle.
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Stern, Alfred M., Thrust reversing variable area nozzle.
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Lair, Jean-Pierre, Toggle interlocked thrust reverser.
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Cariola Roy E., Translating sleeve for cascade type thrust reversing system for fan gas turbine engine for an aircraft.
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Marshall, Richard M.; Gukeisen, Robert L., Tri-body variable area fan nozzle and thrust reverser.
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Barbarin Jacques M. G. (Montivilliers FRX) Lecoutre Pascal B. G. (Le Havre FRX), Turbojet engine thrust reverser with variable exhaust cross-section.
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Duesler Paul W. ; Loffredo Constantino V. ; Prosser ; Jr. Harold T. ; Jones Christopher W., Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems.
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Rey Nancy M. ; Miller Robin M. ; Tillman Thomas G. ; Rukus Robert M. ; Kettle John L. ; Dunphy James R. ; Chaudhry Zaffir A. ; Pearson David D. ; Dreitlein Kenneth C. ; Loffredo Constantino V. ; Wyno, Variable area nozzle for gas turbine engines driven by shape memory alloy actuators.
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Lair,Jean Pierre, Variable cam exhaust nozzle.
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Gonidec Patrick,FRX ; Guy Bernard Vauchel,FRX, Variable cross-section turbofan exhaust duct with door type thrust reverser for aircraft.
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Cariola Roy E. ; Aten Michael R., Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser.
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Konarski Mieczyslaw (Lawrenceburg IN), Variable geometry exhaust nozzle.
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Loffredo Constantino V. ; Szyszko Charles J., Variable geometry exhaust nozzle for a turbine engine.
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Lair,Jean Pierre, Ventilated confluent exhaust nozzle.
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이 특허를 인용한 특허 (9) 인용/피인용 타임라인 분석

Stambaugh, Craig T., Asymmetric load compensation system.
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Aten, Michael Ray; Crawford, Sara, Nacelle.
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Aten, Michael Ray; Crawford, Sara, Nacelle.
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Aten, Michael Ray; Crawford, Sara, Nacelle.
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Aten, Michael Ray; Crawford, Sara, Nacelle.
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Aten, Michael Ray; Crawford, Sara, Nacelle.
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Petty, Dale William, Retractable exhaust liner segment for gas turbine engines.
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Bellanger, Alexandre; Bouillon, Florent; Dubois, Laurent, Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section.
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Gukeisen, Robert L.; Mercier, Claude; Malecki, Robert E., Turbomachine thrust reverser.
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[미국특허] Translating variable area fan nozzle providing an upstream bypass flow exit 원문보기

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[미국특허] Translating variable area fan nozzle providing an upstream bypass flow exit 원문보기

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