WO2008139048A2 - Nacelle pour turboreacteur equipee d'un systeme d'inversion de poussee a une seule porte - Google Patents
Nacelle pour turboreacteur equipee d'un systeme d'inversion de poussee a une seule porte Download PDFInfo
- Publication number
- WO2008139048A2 WO2008139048A2 PCT/FR2008/000454 FR2008000454W WO2008139048A2 WO 2008139048 A2 WO2008139048 A2 WO 2008139048A2 FR 2008000454 W FR2008000454 W FR 2008000454W WO 2008139048 A2 WO2008139048 A2 WO 2008139048A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- door
- nacelle
- downstream
- turbojet
- section
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/56—Reversing jet main flow
- F02K1/58—Reversers mounted on the inner cone or the nozzle housing or the fuselage
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/56—Reversing jet main flow
- F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- Turbojet engine nacelle equipped with a single-door thrust reversal system
- the present invention relates to a turbojet engine nacelle comprising an air intake structure capable of channeling an air flow towards a fan of the turbojet engine, a median structure intended to surround said fan and a downstream section equipped with a system. thrust reverser with pivoting door.
- the role of a thrust reverser during the landing of an aircraft is to improve the braking capacity of an aircraft by redirecting forward at least a portion of the thrust generated by the turbojet engine.
- the inverter obstructs the gas ejection nozzle and directs the ejection flow of the engine towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the engine. the plane.
- the structure of an inverter comprises movable covers movable between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deflected flow, and on the other hand, a position retraction in which they close this passage.
- These mobile hoods may furthermore perform a deflection function or simply the activation of other deflection means.
- the movable hoods slide along rails so that when backing up during the opening phase, they discover deflection vane grids arranged in the thickness of the nacelle .
- a linkage system connects the movable hood to blocking doors that expand within the ejection channel and block the output in direct flow.
- each movable hood pivots so as to block the flow and deflect it and is therefore active in this reorientation.
- Two-door reversers are known which are diametrically opposed to one another and to four gates.
- the document EP 0 131 079 includes a door having a shape of shovel to close off almost the entire ejection section during the inversion phase.
- the downstream part of the door thus has a substantially V-shaped trimming.
- this trimming has several disadvantages. Indeed, the shape of the output section, determined by this trimming downstream end of the door, is not annular, but has notches located substantially at the hinge points of the door.
- US Pat. No. 3,874,620 also discloses a door inverter having only one door.
- a system requires the help of the wing to optimize the flow blocking. It therefore has limitations as to the installation of the nacelle on the aircraft.
- GB 2 075 447 discloses a door inverter comprising a single door and not having clipping problems. This trimming is made unnecessary by the fact that the joints of the door are located as far downstream as possible from the latter, almost at the level of the ejection. In return, it is impossible for said door to block almost all the flow and to effectively reverse it.
- the object of the present invention is to overcome the drawbacks previously mentioned, and in particular to optimize the efficiency of the single-door reversion-thrust systems, and to this end concerns a nacelle for a turbojet engine comprising an input structure of air adapted to channel an air flow to a fan of the turbojet engine, a median structure intended to surround said fan and a downstream section equipped with a pivoting door thrust reversal system, comprising a single thrust reverser door pivotally mounted between a closed position in which it allows a circulation of a flow of air from direct jet engine and in which it ensures the aerodynamic continuity internal and external of the nacelle and an opening position in which it pivots to a position substantially perpendicular to the axis of the nacelle, a downstream portion of said door penetrating the interior of the nacelle for closing at least a portion of the air flow of the turbojet engine and directing it in a direction oriented towards the front of the nacelle, characterized in that the downstream section has, downstream of the door, a
- a downstream peripheral ring makes it possible to overcome the clipping profile of the end of said door.
- the ring has a downstream trimming that can be optimized according to the shape of the desired ejection section and an upstream trimming that will be complementary to the trimming profile of the end of the door.
- the exit section thus eliminates the shape of the door and it will be possible to provide a thin exit section and constant thickness on the ejection periphery. Typically, a thin section will have a thickness of between 3 and 5 mm.
- the closure of the vein is then ensured by the only trimming of the generally concave shaped door, which thus provides a high output section to optimize the performance of the engine in flight and in particular to reduce the fuel consumption.
- the ring forms an ejection nozzle.
- the pivoting door is designed to allow to disengage, upstream of its pivot axis, an inverted jet discharge section approximately equal to twice the section closed by said door in thrust reversal position.
- the presence of a single door of thrust reversal implies to provide a door larger than traditional multi-port systems to ensure a thrust reversal efficiency close to traditional multi-port systems. It follows that this larger door releases, when it opens, a corresponding larger hole in the nacelle. Access to the interior of the nacelle for carrying out maintenance operations is greatly facilitated.
- the thrust reversal system comprises a single means for actuating the door fixed upstream of the latter substantially at a median longitudinal axis.
- the thrust reversal system comprises means for locking the door in the closed position in the form of a shear pin capable of cooperating with a corresponding bore formed in the thickness of the door.
- the bore has a diameter greater than the diameter of the corresponding shear pin and is located eccentrically with respect to said pin so that in the closed position, the pin comes to exert pressure against an inner surface of the bore and requires an over-retraction to be engaged and / or clear without effort.
- the downstream section has a fixed structure comprising an outer surface and an inner surface, said inner surface and / or said outer surface being each made in one piece, the fixed structure then being preferentially obtained by interlocking the two substantially frustoconical forms.
- the downstream section has, upstream of the door, a front frame extending over the entire periphery of the downstream section.
- the present invention also relates to an aircraft characterized in that it is equipped with at least one pair of propulsion units each comprising a turbojet engine housed in a nacelle according to the invention, each propulsion unit of each pair being disposed symmetrically with respect to a longitudinal axis of the aircraft.
- the nacelles are oriented so as to allow their doors to open in a direction normal to the fuselage.
- a nacelle according to the present invention ensuring a reorientation of its ejection flow only with the aid of the inverter door, the system is freed from a wing or other element of the aircraft and may be integrated in any place of the latter.
- FIG. 1 is a diagrammatic representation in front view of an aircraft equipped with two propulsion units arranged on either side of the fuselage and each comprising a nacelle according to the invention.
- Figure 2 is a schematic perspective view of a downstream section of a nacelle according to the invention having the thrust reversal door in the open position.
- FIG. 3 is a diagrammatic representation in side view of the downstream section of FIG. 2.
- FIG. 4 is a schematic rear view of the downstream section of FIG. 2.
- FIG. 5 is a diagrammatic view in side view of the downstream section of FIG. 3 showing the thrust reversal door in the closed position. .
- FIG. 6 is a schematic representation of a locking system particularly intended for the downstream section of FIGS. 2 to 5.
- a nacelle 1 according to the invention as shown in Figure 1 mounted on an aircraft A, is a tubular housing for a turbojet (not visible) which it serves to channel the air flow or it generates.
- the nacelle 1 is more particularly intended to be fixed on one side of the fuselage of the aircraft via a pylon 2.
- the nacelle 1 has a structure comprising a front section forming an air inlet, a downstream section surrounding a fan of the turbojet engine and a downstream section 10 surrounding the turbojet engine and housing a reversing system. thrust.
- This downstream section 10 may be extended by an ejection nozzle section.
- the downstream section 10 has a substantially tubular and frustoconical shape comprising a fixed structure 11 having an outer surface 12 and an inner surface 13 connected upstream by a peripheral front frame 14 and joining downstream in a single plane by a thin section and constant.
- This fixed structure 11 has a recess defining a lateral opening 15 on which pivot axes 16 supporting a door 17 are mounted.
- Said door 17 is adapted to tilt about an axis defined by the pivot axes 16 between a first closed position in which it closes the lateral opening 15 and ensures the aerodynamic continuity of the outer surface 12 and the inner surface 13 of the fixed structure 11 and an open position in which a downstream portion 17a of the door 17 penetrates at least partially inside the downstream section, thus being able to block a part of the direct jet air flow and directing it through the opening 15 where an upstream portion 17b of the door 17 completes its reorientation in a forward direction of the nacelle 1.
- opening 15 and a location of the pivot axes 16 calculated so that the thrust reversal section of the turbojet will be defined.
- opening 15, that is to say substantially the section of the upstream portion 17b of the door 17 is substantially equal to twice the section of the downstream portion 17a of the door 17 closing the downstream section 10.
- this surface ratio is only given as an example and can be adapted according to the operating data of the turbojet engine.
- the door 17 is actuated by means of an actuator (not shown) of the hydraulic, pneumatic or electric cylinder type having a first end fixed in the door 17 and a second end secured to the fixed part 11, preferably mounted on the front frame 14.
- the first end is fixed at a central longitudinal axis of the door 17.
- the downstream section 10 is also equipped with locking means of the door 17 in the closed position.
- the locking system is shown in more detail in FIG.
- Each locking system comprises a shear pin 20 mounted to move in translation in a direction perpendicular to the front frame 14.
- This shear pin 20 is adapted to cooperate with a corresponding bore 21 formed in the thickness of the door 17.
- the shear pin 20 is actuated to enter the corresponding bore 21.
- the door 17 is then locked in rotation.
- the door 17 cooperates with two locking systems each disposed at one end of said door 17.
- a shear pin locking system allowing over-retraction can be applied to other moving parts of the nacelle, including access hatches. It is understood from the description that the nacelle 1 according to the invention having a downstream section 10 as described can be equipped with lighter actuating and locking system, so more economical.
- a downstream section 10 has a large fixed structure 11 that can advantageously be made from a reduced number of elements to limit the assembly of said elements and resulting aerodynamic accidents.
- An advantageous method for producing said fixed structure will be to produce in one piece each of the outer surface 12 and the inner surface 13.
- the general shape of each of these two surfaces 12, 13 being frustoconical, they can be easily fitted together. one in the other. It is then sufficient simply to finish the fixed structure 11 by connecting the two surfaces 12, 13 upstream by the front frame 14 and downstream after fitting each nested piece to each other.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/594,750 US20100115916A1 (en) | 2007-04-12 | 2008-04-02 | Nacelle for turbojet jet fitted with a single door thrust reverser system |
CA002680265A CA2680265A1 (fr) | 2007-04-12 | 2008-04-02 | Nacelle pour turboreacteur equipee d'un systeme d'inversion de poussee a une seule porte |
BRPI0810535-9A2A BRPI0810535A2 (pt) | 2007-04-12 | 2008-04-02 | Nacela para turbojato e avião. |
EP08787893A EP2132427A2 (fr) | 2007-04-12 | 2008-04-02 | Nacelle pour turboreacteur equipee d'un systeme d'inversion de poussee a une seule porte |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0702658 | 2007-04-12 | ||
FR0702658A FR2914956A1 (fr) | 2007-04-12 | 2007-04-12 | Nacelle pour turboreacteur equipee d'un systeme d'inversion de poussee a porte |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2008139048A2 true WO2008139048A2 (fr) | 2008-11-20 |
WO2008139048A3 WO2008139048A3 (fr) | 2009-01-29 |
Family
ID=38805720
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2008/000454 WO2008139048A2 (fr) | 2007-04-12 | 2008-04-02 | Nacelle pour turboreacteur equipee d'un systeme d'inversion de poussee a une seule porte |
Country Status (8)
Country | Link |
---|---|
US (1) | US20100115916A1 (fr) |
EP (1) | EP2132427A2 (fr) |
CN (1) | CN101657629A (fr) |
BR (1) | BRPI0810535A2 (fr) |
CA (1) | CA2680265A1 (fr) |
FR (1) | FR2914956A1 (fr) |
RU (1) | RU2009140916A (fr) |
WO (1) | WO2008139048A2 (fr) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2955154B1 (fr) | 2010-01-08 | 2012-01-06 | Airbus Operations Sas | Inverseur de poussee pour aeronef a turboreacteurs a double flux semi-enterres |
FR2959531B1 (fr) | 2010-04-28 | 2015-12-18 | Aircelle Sa | Inverseur a portes |
FR3062637B1 (fr) * | 2017-02-07 | 2020-07-10 | Airbus Operations (S.A.S.) | Nacelle de turboreacteur comportant un mecanisme d'entrainement d'inverseur de poussee |
US11396854B2 (en) * | 2017-10-25 | 2022-07-26 | Rohr, Inc. | Hinge mechanism for pivot door thrust reversers |
FR3077606B1 (fr) * | 2018-02-05 | 2020-01-17 | Airbus | Nacelle d'un turboreacteur comportant une porte exterieure d'inversion |
FR3079878A1 (fr) * | 2018-04-05 | 2019-10-11 | Airbus Operations | Turboreacteur comportant une nacelle equipee d'un systeme inverseur comportant un capot articule |
FR3080651B1 (fr) * | 2018-04-25 | 2020-04-24 | Safran Nacelles | Inverseur de poussee avec systeme d’ouverture et de fermeture optimise |
US11719188B2 (en) * | 2018-05-15 | 2023-08-08 | Gulfstream Aerospace Corporation | Thrust reverser with continuous curved surface |
US11142330B2 (en) * | 2018-08-30 | 2021-10-12 | Aurora Flight Sciences Corporation | Mechanically-distributed propulsion drivetrain and architecture |
FR3088373B1 (fr) * | 2018-11-09 | 2021-03-19 | Safran Nacelles | Joint d’etancheite pour nacelle de turboreacteur d’aeronef |
US11155343B2 (en) * | 2018-12-17 | 2021-10-26 | The Boeing Company | Brake systems for aircraft and related methods |
FR3091855A1 (fr) * | 2019-01-22 | 2020-07-24 | Airbus Operations | NACELLE D’UN TURBOREACTEUR COMPORTANT UN ensemble mobile ET UNe structure fixe renforcee |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3874620A (en) * | 1973-03-09 | 1975-04-01 | Boeing Co | Reversing apparatus for a jet engine |
GB2075447A (en) * | 1980-04-30 | 1981-11-18 | Rolls Royce | Thrust deflectors for gas turbine engines |
EP0131079A1 (fr) * | 1982-05-17 | 1985-01-16 | Societe De Construction Des Avions Hurel-Dubois | Inverseur de poussée à porte notamment pour moteur d'avion à réaction |
WO1996038661A1 (fr) * | 1995-06-02 | 1996-12-05 | Societe De Construction Des Avions Hurel-Dubois | Ensemble d'inverseur de poussee a deux portes |
WO1999004118A1 (fr) * | 1997-07-20 | 1999-01-28 | Avganim, Alexander, Gad | Dispositif de verrouillage pour portes ou volets coulissants |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1002709A (en) * | 1964-02-03 | 1965-08-25 | Rolls Royce | Improvements in or relating to thrust reversers for jet propulsion engines |
GB1127828A (en) * | 1966-06-29 | 1968-09-18 | Rolls Royce | Fan thrust reverser for jet propulsion plant |
US3570767A (en) * | 1969-10-01 | 1971-03-16 | Rohr Corp | Thrust reversing apparatus |
US5039171A (en) * | 1989-08-18 | 1991-08-13 | Societe Anonyme Dite Hispano-Suiza | Multi-panel thrust reverser door |
IT1257222B (it) * | 1992-06-09 | 1996-01-10 | Alenia Aeritalia & Selenia | Dispositivo inversore di spinta per motori aeronautici a getto. |
FR2721977B1 (fr) * | 1994-06-30 | 1996-08-02 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a double flux a obstacles lies au capot primaire |
FR2737256B1 (fr) * | 1995-07-26 | 1997-10-17 | Aerospatiale | Turboreacteur a double flux a portes d'inversion de poussee non soumises au flux secondaire dans leur position inactive |
EP0763654B1 (fr) * | 1995-09-13 | 1999-12-29 | SOCIETE DE CONSTRUCTION DES AVIONS HUREL-DUBOIS (société anonyme) | Système électro-hydraulique pour inverseur de pourré à deux portes |
FR2742482B1 (fr) * | 1995-12-19 | 1998-02-06 | Hurel Dubois Avions | Inverseur de poussee a tuyere a section reglable pour moteur d'avion a reaction |
EP0789140B1 (fr) * | 1996-02-08 | 2001-11-07 | Societe De Construction Des Avions Hurel-Dubois | Dispositif d'étanchéité pour porte basculante d'inverseur de poussée |
EP0852290A1 (fr) * | 1996-12-19 | 1998-07-08 | SOCIETE DE CONSTRUCTION DES AVIONS HUREL-DUBOIS (société anonyme) | Inverseur de poussée de turboréacteur à double flux avec grand taux de dilution |
US5875995A (en) * | 1997-05-20 | 1999-03-02 | Rohr, Inc. | Pivoting door type thrust reverser with deployable members for efflux control and flow separation |
US6487845B1 (en) * | 2001-06-08 | 2002-12-03 | The Nordam Group, Inc. | Pivot fairing thrust reverser |
US7146796B2 (en) * | 2003-09-05 | 2006-12-12 | The Nordam Group, Inc. | Nested latch thrust reverser |
FR2912189B1 (fr) * | 2007-02-01 | 2012-02-17 | Airbus France | Nacelle d'aeronef incorporant un dispositif pour inverser la poussee |
US8002217B2 (en) * | 2007-11-16 | 2011-08-23 | Spirit Aerosystems, Inc. | System for adjustment of thrust reverser pivot door |
-
2007
- 2007-04-12 FR FR0702658A patent/FR2914956A1/fr not_active Withdrawn
-
2008
- 2008-04-02 US US12/594,750 patent/US20100115916A1/en not_active Abandoned
- 2008-04-02 WO PCT/FR2008/000454 patent/WO2008139048A2/fr active Application Filing
- 2008-04-02 BR BRPI0810535-9A2A patent/BRPI0810535A2/pt not_active Application Discontinuation
- 2008-04-02 CA CA002680265A patent/CA2680265A1/fr not_active Abandoned
- 2008-04-02 RU RU2009140916/06A patent/RU2009140916A/ru unknown
- 2008-04-02 CN CN200880011729A patent/CN101657629A/zh active Pending
- 2008-04-02 EP EP08787893A patent/EP2132427A2/fr not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3874620A (en) * | 1973-03-09 | 1975-04-01 | Boeing Co | Reversing apparatus for a jet engine |
GB2075447A (en) * | 1980-04-30 | 1981-11-18 | Rolls Royce | Thrust deflectors for gas turbine engines |
EP0131079A1 (fr) * | 1982-05-17 | 1985-01-16 | Societe De Construction Des Avions Hurel-Dubois | Inverseur de poussée à porte notamment pour moteur d'avion à réaction |
WO1996038661A1 (fr) * | 1995-06-02 | 1996-12-05 | Societe De Construction Des Avions Hurel-Dubois | Ensemble d'inverseur de poussee a deux portes |
WO1999004118A1 (fr) * | 1997-07-20 | 1999-01-28 | Avganim, Alexander, Gad | Dispositif de verrouillage pour portes ou volets coulissants |
Also Published As
Publication number | Publication date |
---|---|
WO2008139048A3 (fr) | 2009-01-29 |
US20100115916A1 (en) | 2010-05-13 |
CN101657629A (zh) | 2010-02-24 |
FR2914956A1 (fr) | 2008-10-17 |
RU2009140916A (ru) | 2011-05-20 |
BRPI0810535A2 (pt) | 2014-10-21 |
EP2132427A2 (fr) | 2009-12-16 |
CA2680265A1 (fr) | 2008-11-20 |
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