RU97105831A - DEVICE REVERSE DEVICE FOR TWO-CIRCUIT TURBOREACTIVE ENGINE WITH ASYMMETRIC Sashes - Google Patents

DEVICE REVERSE DEVICE FOR TWO-CIRCUIT TURBOREACTIVE ENGINE WITH ASYMMETRIC Sashes

Info

Publication number
RU97105831A
RU97105831A RU97105831/06A RU97105831A RU97105831A RU 97105831 A RU97105831 A RU 97105831A RU 97105831/06 A RU97105831/06 A RU 97105831/06A RU 97105831 A RU97105831 A RU 97105831A RU 97105831 A RU97105831 A RU 97105831A
Authority
RU
Russia
Prior art keywords
turbojet engine
thrust
flaps
width
circuit
Prior art date
Application number
RU97105831/06A
Other languages
Russian (ru)
Other versions
RU2134358C1 (en
Inventor
Ларди Паскаль
Бернар Вошель Ги
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 FR9508410A external-priority patent/FR2736682B1/en
Application filed by Сосьете Испано-Сюиза filed Critical Сосьете Испано-Сюиза
Publication of RU97105831A publication Critical patent/RU97105831A/en
Application granted granted Critical
Publication of RU2134358C1 publication Critical patent/RU2134358C1/en

Links

Claims (4)

1. Устройство реверсирования тяги двухконтурного турбореактивного двигателя, содержащее поворотные створки (27, 37; 107, 117, 127, 137), выполненные с возможностью в закрытом положении, то есть при функционировании силовой установки в режиме прямой тяги, соединения с наружной стенкой канала вторичного потока позади вентилятора данного турбореактивного двигателя, причем каждая из створок выполнена с возможностью поворота от приводного средства, управляющего перемещением створок таким образом, чтобы образовать препятствия отклонения потока в процессе функционирования данного устройства в режиме реверсированной тяги, отличающееся тем, что ширина (25, 32, 33) створок, располагающихся с определенной стороны (27, 107, 117), выполнена уменьшенной по отношению к ширине (26, 346 35) створок (37, 127, 137), располагающихся с противоположной стороны по отношению к геометрической оси вращения данного турбореактивного двигателя.1. The device for reversing the thrust of a bypass turbojet engine containing rotary flaps (27, 37; 107, 117, 127, 137), made with the possibility in the closed position, that is, when the power plant is operating in direct thrust mode, the connection with the outer wall of the secondary channel flow behind the fan of this turbojet engine, and each of the valves is rotatable from the drive means that controls the movement of the valves in such a way as to form obstacles to the deviation of the flow in the process of functioning of this device in reverse thrust mode, characterized in that the width (25, 32, 33) of the flaps located on a certain side (27, 107, 117) is made reduced in relation to the width (26, 346 35) of the flaps (37 , 127, 137), located on the opposite side with respect to the geometric axis of rotation of the turbojet engine. 2. Устройство реверсирования тяги двухконтурного турбореактивного двигателя по п. 1, отличающееся тем, что силовая установка, содержащая турбореактивный двигатель, установлена под крылом самолета, и данное устройство реверсирования тяги содержит четыре створки, причем ширина (25, 32, 33) верхних створок (27, 107, 117) выполнена уменьшенной по отношению к ширине (36 34, 35) нижних створок (37, 127, 137) таким образом, чтобы обеспечить в режиме реверсирования тяги расход газов, истекающих в направлении вверх, менее значительный, чем расход газов, истекающих в направлении вниз. 2. The thrust reversal device of a dual-circuit turbojet engine according to claim 1, characterized in that the power plant containing the turbojet engine is installed under the wing of the aircraft, and this thrust reversal device contains four wings, the width (25, 32, 33) of the upper wings ( 27, 107, 117) is made reduced in relation to the width (36 34, 35) of the lower flaps (37, 127, 137) in such a way as to ensure that in the thrust reversal mode the flow of gases flowing upward is less significant than the gas flow expiring in on systematic way down. 3. Устройство реверсирования тяги двухконтурного турбореактивного двигателя в соответствии с п. 2, отличающееся тем, что соответствующие значения ширины (32, 33) верхних створок (107, 117) отличаются друг от друга. 3. The thrust reverser of a dual-circuit turbojet engine in accordance with paragraph 2, characterized in that the corresponding widths (32, 33) of the upper flaps (107, 117) are different from each other. 4. Устройство реверсирования тяги двухконтурного турбореактивного двигателя в соответствии с одним из пунктов 2 или 3, отличающееся тем, что соответствующие значения ширины (34, 35) нижних створок (127, 127) отличаются друг от друга. 4. The thrust reverser of a dual-circuit turbojet engine in accordance with one of paragraphs 2 or 3, characterized in that the corresponding widths (34, 35) of the lower flaps (127, 127) are different from each other.
RU97105831A 1995-07-12 1996-07-11 Doubler-flow turbojet engine thrust reverser with asymmetrical flaps RU2134358C1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR9508410A FR2736682B1 (en) 1995-07-12 1995-07-12 DOUBLE FLOW TURBOMACHINE DRIVE INVERTER WITH DISSYMMETRIC DOORS
FR9508410 1995-07-12
PCT/FR1996/001078 WO1997003284A1 (en) 1995-07-12 1996-07-11 Turbofan engine thrust reverser with asymmetrical doors

Publications (2)

Publication Number Publication Date
RU97105831A true RU97105831A (en) 1999-03-27
RU2134358C1 RU2134358C1 (en) 1999-08-10

Family

ID=9480909

Family Applications (1)

Application Number Title Priority Date Filing Date
RU97105831A RU2134358C1 (en) 1995-07-12 1996-07-11 Doubler-flow turbojet engine thrust reverser with asymmetrical flaps

Country Status (8)

Country Link
US (1) US5727380A (en)
EP (1) EP0754849B1 (en)
JP (1) JPH09100747A (en)
CA (1) CA2180818A1 (en)
DE (1) DE69607793T2 (en)
FR (1) FR2736682B1 (en)
RU (1) RU2134358C1 (en)
WO (1) WO1997003284A1 (en)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100398417B1 (en) * 1999-08-10 2003-09-19 주식회사 포스코 A method for treating electrogalvanizing wastewaters
KR100430333B1 (en) * 2002-05-03 2004-05-04 윤취주 Method for Preparing Sodium Nitrate Using Waste Nitric Acid
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
US7797944B2 (en) 2006-10-20 2010-09-21 United Technologies Corporation Gas turbine engine having slim-line nacelle
US7870721B2 (en) 2006-11-10 2011-01-18 United Technologies Corporation Gas turbine engine providing simulated boundary layer thickness increase
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
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
US7735778B2 (en) 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8051639B2 (en) * 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8186942B2 (en) * 2007-12-14 2012-05-29 United Technologies Corporation Nacelle assembly with turbulators
US8192147B2 (en) * 2007-12-14 2012-06-05 United Technologies Corporation Nacelle assembly having inlet bleed
DE102015206143A1 (en) * 2015-04-07 2016-10-13 Rolls-Royce Deutschland Ltd & Co Kg Device for influencing floor vortices in the intake area of an aircraft gas turbine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3097484A (en) * 1960-06-13 1963-07-16 Thrust reversers for jet engines
US3279182A (en) * 1965-06-07 1966-10-18 Gen Electric Thrust reverser
FR1482538A (en) * 1965-06-07 1967-05-26 Gen Electric Thrust reverser
GB1181746A (en) * 1968-06-19 1970-02-18 Rolls Royce Thrust Reverser for Jet Propulsion Plant
US3640468A (en) * 1970-03-30 1972-02-08 Lockheed Aircraft Corp Thrust reverser for asymmetric exhaust efflux deflection
US3605411A (en) * 1970-07-01 1971-09-20 Rohr Corp Thrust reversing apparatus
GB2075447B (en) * 1980-04-30 1983-10-26 Rolls Royce Thrust deflectors for gas turbine engines
FR2486153B1 (en) * 1980-07-04 1985-10-04 Hurel Dubois Avions DRIVE INVERTER FOR A REACTION ENGINE, IN PARTICULAR FOR EQUIPPING AN AIRCRAFT
FR2618853B1 (en) * 1987-07-29 1989-11-10 Hispano Suiza Sa TURBOREACTOR DRIVE INVERTER WITH MOBILE DOOR DEFLECTOR
US5230213A (en) * 1991-06-12 1993-07-27 Rohr, Inc. Aircraft turbine engine thrust reverser
FR2680547B1 (en) * 1991-08-21 1993-10-15 Hispano Suiza TURBOREACTOR DRIVE INVERTER HAVING A DEVIATION EDGE WITH EVOLUTIVE CURVATURE.
FR2681101B1 (en) * 1991-09-11 1993-11-26 Hispano Suiza PUSH INVERTER WITH IMPROVED PILOTAGE OF REVERSE FLOW PATCHES.

Similar Documents

Publication Publication Date Title
RU97105831A (en) DEVICE REVERSE DEVICE FOR TWO-CIRCUIT TURBOREACTIVE ENGINE WITH ASYMMETRIC Sashes
RU2138667C1 (en) Turbojet engine clamshell trust reverser with rear hinged panel
RU2449151C2 (en) Car for aircraft and aircraft equipped with such car
US4030291A (en) Thrust reverser for a gas turbofan engine
RU2101534C1 (en) Turbojet engine thrust reverser
RU2162538C2 (en) Turbojet-engine thrust-reversal unit with doors forming buckets coupled with movable deflector
US4005822A (en) Fan duct thrust reverser
RU2499904C2 (en) Bypass turbojet nacelle
US5211008A (en) Gas ejection nozzle for a jet engine and a jet engine fitted with this nozzle, in particular an engine of the separate flow type
JPS648347A (en) Two-dimensional type exhaust nozzle
JPS61112769A (en) Two-dimensional variable area exhaust nozzle for gas turbineengine
EP0809011A2 (en) Multiaxis thrust-vectoring for turbo-fan engines
RU2139434C1 (en) Thrust reversal unit of turbojet engine with doors provided with deflecting blades
RU2136934C1 (en) Device for reversing thrust of double-flow turbojet engine with doors connected with bearing panel
CN1014260B (en) Gas flow diverter
RU2134358C1 (en) Doubler-flow turbojet engine thrust reverser with asymmetrical flaps
KR970047374A (en) Air conditioner and its control method
RU98112764A (en) DEVICE REVERSE DEVICE WITH TURNING DOORS WITH CONTROLLED LEAKAGE COSTS
JPH1071998A (en) Thrust reversing device for turbojet engine with door forming rake part
RU2162537C2 (en) Turbojet-engine thrust reversal unit whose doors form buckets coupled with movable first-in-flow fairing
US4767055A (en) Method and linkage for positioning a convergent flap and coaxial arc valve
JPH04228838A (en) Passive by-pass valve assembly
GB1092015A (en) Improvements in thrust reversers for jet propulsion power plants
US3262269A (en) Thrust reverser
JPH10122046A (en) Leakage flow-controlling gate type thrust inverter