RU96122637A - DEVICE REVERSE DEVICE FOR TURBOJET ENGINE WITH REAR LOCATED Sashes - Google Patents

DEVICE REVERSE DEVICE FOR TURBOJET ENGINE WITH REAR LOCATED Sashes

Info

Publication number
RU96122637A
RU96122637A RU96122637/06A RU96122637A RU96122637A RU 96122637 A RU96122637 A RU 96122637A RU 96122637/06 A RU96122637/06 A RU 96122637/06A RU 96122637 A RU96122637 A RU 96122637A RU 96122637 A RU96122637 A RU 96122637A
Authority
RU
Russia
Prior art keywords
turbojet engine
thrust
shutter
rotary axes
turbojet
Prior art date
Application number
RU96122637/06A
Other languages
Russian (ru)
Other versions
RU2124646C1 (en
Inventor
Жорж Валлерой Лоран
Original Assignee
Сосьете Испано-Сюиза
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from FR9501959A external-priority patent/FR2730763B1/en
Application filed by Сосьете Испано-Сюиза filed Critical Сосьете Испано-Сюиза
Application granted granted Critical
Publication of RU2124646C1 publication Critical patent/RU2124646C1/en
Publication of RU96122637A publication Critical patent/RU96122637A/en

Links

Claims (2)

1. Устройство реверсирования тяги двухконтурного турбореактивного двигателя, содержащее подвижные элементы или створки /20/, выполненные с возможностью соединения турбореактивного двигателя в режиме прямой тяги с наружной стенкой /14/ кольцевого канала вторичного потока, образуя при этом задний по потоку конец выпускной трубы вентилятора данного турбореактивного двигателя, и способные в своем развернутом положении образовать препятствия, предназначенные для отклонения вторичного потока газов и обеспечивающие реверсирование тяги турбореактивного двигателя, причем створки /20/ установлены с возможностью вращения на поворотных осях /21/ и связаны со средствами перемещения, отличающееся тем, что каждая створка /20/ соединена в своей задней части при помощи, по меньшей мере, одной тяги /23/ с внутренней неподвижной конструкцией /18/ вторичного канала, причем поворотные оси /21/ подвижной створки расположены на подвижных скользящих каретках /22/, выполненных с возможностью скольжения назад по потоку вдоль направления, параллельного продольной геометрической оси турбореактивного двигателя в процессе перехода упомянутых створок /20/ в развернутое положение, соответствующее реверсированию тяги данного турбореактивного двигателя, при этом в режиме прямой тяги стык между передней по потоку внутренней кромкой створки /20/ и наружной в радиальном направлении неподвижной конструкцией /19/ имеет неразрывный аэродинамический профиль, не имеющий никаких полостей.1. A device for reversing the thrust of a bypass turbojet engine containing movable elements or flaps / 20 /, configured to connect the turbojet engine in direct thrust mode with the outer wall / 14 / of the annular channel of the secondary stream, thereby forming a downstream end of the exhaust pipe of the fan of this turbojet engine, and capable in its deployed position to form obstacles designed to deflect the secondary gas flow and providing reverse turbine thrust a jet engine, and the shutters / 20 / are mounted for rotation on rotary axes / 21 / and are connected with means of movement, characterized in that each shutter / 20 / is connected in its rear part using at least one rod / 23 / with an internal fixed structure / 18 / of the secondary channel, the pivoting axes / 21 / of the movable sash being located on movable sliding carriages / 22 /, made with the possibility of sliding backward along the flow along a direction parallel to the longitudinal geometric axis of the turbojet during the transition of the said leaves / 20 / to the deployed position, corresponding to reversing the thrust of a given turbojet engine, while in the direct thrust mode, the joint between the upstream inner edge of the sash / 20 / and the radially outer stationary structure / 19 / has an inextricable aerodynamic a profile that does not have any cavities. 2. Устройство реверсирования тяги двухконтурного турбореактивного двигателя п. 1, отличающееся тем, что створки /20/ предусмотрены в количестве четырех и каждая такая створка /20/ связана с двумя поворотными осями /21/, каждая из которых располагается на боковой кромке данной створки, и на каждой скользящей каретке /22/ располагаются две поворотных оси /21/, связанных соответственно с двумя соседними створками /20/. 2. The thrust reverser of a dual-circuit turbojet engine of claim 1, characterized in that the shutters / 20 / are provided in an amount of four and each such shutter / 20 / is connected with two rotary axes / 21 /, each of which is located on the lateral edge of the shutter, and on each sliding carriage / 22 / there are two rotary axes / 21 /, connected respectively with two adjacent wings / 20 /.
RU96122637A 1995-02-21 1996-02-15 Draft reversing device for turbojet engine with rear doors RU2124646C1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR9501959 1995-02-21
FR9501959A FR2730763B1 (en) 1995-02-21 1995-02-21 DOWNSTREAM SHUTTER REVERSER FOR TURBOJET
PCT/FR1996/000249 WO1996026359A1 (en) 1995-02-21 1996-02-15 Thrust reverser with downstream flaps for turbojet engines

Publications (2)

Publication Number Publication Date
RU2124646C1 RU2124646C1 (en) 1999-01-10
RU96122637A true RU96122637A (en) 1999-01-20

Family

ID=9476336

Family Applications (1)

Application Number Title Priority Date Filing Date
RU96122637A RU2124646C1 (en) 1995-02-21 1996-02-15 Draft reversing device for turbojet engine with rear doors

Country Status (8)

Country Link
US (1) US5725182A (en)
EP (1) EP0728934B1 (en)
JP (1) JPH08240150A (en)
CA (1) CA2169874C (en)
DE (1) DE69602296T2 (en)
FR (1) FR2730763B1 (en)
RU (1) RU2124646C1 (en)
WO (1) WO1996026359A1 (en)

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US8408491B2 (en) * 2007-04-24 2013-04-02 United Technologies Corporation Nacelle assembly having inlet airfoil for a gas turbine engine
US8205430B2 (en) * 2007-05-16 2012-06-26 United Technologies Corporation Variable geometry nacelle assembly for a gas turbine engine
US8402739B2 (en) * 2007-06-28 2013-03-26 United Technologies Corporation Variable shape inlet section for a nacelle assembly of a gas turbine engine
US9004399B2 (en) * 2007-11-13 2015-04-14 United Technologies Corporation Nacelle flow assembly
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US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8051639B2 (en) * 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US8192147B2 (en) * 2007-12-14 2012-06-05 United Technologies Corporation Nacelle assembly having inlet bleed
US8186942B2 (en) * 2007-12-14 2012-05-29 United Technologies Corporation Nacelle assembly with turbulators
US8959889B2 (en) 2008-11-26 2015-02-24 The Boeing Company Method of varying a fan duct nozzle throat area of a gas turbine engine
US8127532B2 (en) * 2008-11-26 2012-03-06 The Boeing Company Pivoting fan nozzle nacelle
FR2959488B1 (en) 2010-04-28 2012-05-18 Aircelle Sa NACELLE FOR AN AIRCRAFT ENGINE WITH THRUST INVERTER WITH GRIDS AND ADAPTIVE TUBE
US9038367B2 (en) 2011-09-16 2015-05-26 United Technologies Corporation Fan case thrust reverser
US9097209B2 (en) 2012-03-27 2015-08-04 United Technologies Corporation Gas turbine engine thrust reverser system
US9631578B2 (en) 2013-02-22 2017-04-25 United Technologies Corporation Pivot thrust reverser surrounding inner surface of bypass duct
US9617009B2 (en) 2013-02-22 2017-04-11 United Technologies Corporation ATR full ring sliding nacelle
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