WO2009066037A1 - Inverseur de poussee a grilles - Google Patents
Inverseur de poussee a grilles Download PDFInfo
- Publication number
- WO2009066037A1 WO2009066037A1 PCT/FR2008/001264 FR2008001264W WO2009066037A1 WO 2009066037 A1 WO2009066037 A1 WO 2009066037A1 FR 2008001264 W FR2008001264 W FR 2008001264W WO 2009066037 A1 WO2009066037 A1 WO 2009066037A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rear frame
- acoustic panel
- thrust reverser
- pads
- plates
- 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
- F02K1/64—Reversing fan flow
- F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
- F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
-
- 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
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/827—Sound absorbing structures or liners
-
- 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
- FIGS. 1 and 2 attached hereto show a prior art thrust reverser in the direct jet position.
- such a thrust reverser comprises:
- a mobile structure comprising an outer wall, an inner wall formed in part by at least one acoustic panel, and at least one partition connecting said outer wall to said acoustic panel; actuators 16 interposed between said structure; fixed 1 and said movable structure 7, extending through orifices 17, 19 respectively formed in said rear frame 3 and said partition 15.
- the thrust reverser is shown in a direct jet configuration.
- the air coming from the upstream of the thrust reverser that is to say from the left of FIG. 2 circulates in the vein 21 located between the mobile structure 7 and a fixed internal structure 23, downstream of the thrust reverser, that is to say to the right of Figure 2, as indicated by the arrow F1.
- Connecting rods 25 connect movable panels 27 situated opposite grids 5 and articulated on movable structure 7, to fixed internal structure 23.
- the radial thickness of the movable structure 7 in the region of the grids 5 should be as small as possible; this is particularly critical in the case of large nacelles, such as those for jet engines Airbus A380.
- this reduction in thickness is limited in particular by the radial thickness of the rear frame 3, and by a minimum radial distance d between this rear frame and the acoustic panel 13.
- the radial thickness of the rear frame 3 can not fall below a threshold without risk of dangerously weakening the entire thrust reverser, and the minimum distance d prevents the acoustic panel 13 from entering into operation. contact with the rear frame. It is therefore understood that, in a conventional grid inverter, the radial thickness of the movable portion 7 in the grid area can not fall below a certain threshold.
- the present invention is intended to provide a solution for lowering this threshold, and thus improve the aerodynamic performance of the propulsion system.
- a grid thrust reverser comprising:
- a movable structure comprising an outer wall, an inner wall formed at least in part by at least one acoustic panel, and at least one partition connecting said outer wall to said panel; acoustic, and
- actuators interposed between said fixed structure and said movable structure, extending through orifices formed in said rear frame and said partition, characterized in that said rear frame and said acoustic panel are sufficiently radially close to one of the another to interfere mutually and in a controlled manner when said structure is in the direct jet position.
- the expression “mutually interfering” designates a direct as well as an indirect contact (that is to say, via additional pieces) of the rear frame on the acoustic panel.
- said rear frame comprises, in its zone of interference with said acoustic panel, contact pads with this panel: these contact pads make it possible to precisely locate the contact areas of the rear frame on the acoustic panel, and thus contribute to the good control of the interference in these organs;
- said acoustic panel comprises, in its zone of interference with said rear frame, contact plates with this rear frame: these contact plates make it possible to precisely locate the contact zones of the acoustic panel on the rear frame, and thus contribute the good control of the interference between these organs;
- said pads and said plates are arranged in such a way as to mutually cooperate: the simultaneous presence of these pads and of these plates allows an optimal control of the interference between the rear frame and the acoustic panel;
- said contact pads are arranged on the downstream part of said rear frame, the upstream part of this rear frame is shaped so as to have, at least in the circumferential zones in which said pads are situated, a radial distance with respect to said acoustic panel; , or where appropriate with respect to the plates, which is greater than the radial distance separating said pads from this acoustic panel, or, if appropriate, said plates: this arrangement makes it possible to avoid the risk that the upstream part of the rear frame comes into contact with the acoustic panel or, where appropriate, with the plates, and thus to locate the interference zone of the rear frame with the acoustic panel exclusively in the downstream part of this rear frame;
- said acoustic panel comprises hollow zones allowing the passage of said actuators, and said pads are placed in such a way as to cooperate with said hollow zones: these recessed zones are zones of greater strength of the acoustic panel, and therefore allow to limit any risk of degradation of the acoustic panel under the effect of the contact of the rear frame;
- said rear frame is formed of composite material
- the present invention also relates to an aircraft nacelle equipped with a grid thrust reverser according to any one of the preceding claims.
- FIG. 1 is a perspective view of a prior art half-gate thrust reverser, in a direct jet configuration, mentioned in the preamble of the present description,
- FIG. 2 is a sectional view of the inverter of FIG. 1 taken along the plane II of this FIG.
- FIG. 3 is a detail view of an area similar to zone III of FIG. 2, for a gate thrust reverser according to the invention
- FIG. 4 shows in perspective the connection zone of the partition 15 on the acoustic panel 13, for a gate thrust reverser according to the invention.
- FIG. 5 represents a view of this partition and of this acoustic panel in the direction V of FIG. 4.
- the rear grid frame 3 may be seen having a plurality of circumferentially spaced orifices 17 (typically 2 or 3 per side).
- the rear frame 3 has substantially a U-shaped profile whose lower branch 29 has on its face located opposite the acoustic panel 13, a plurality of pads 31 spaced circumferentially evenly and / or appropriately placed where the interference between the rear frame and the acoustic panel are the most important.
- These pads 31 are dimensioned so as to constitute the contact areas of the lower branch 29 of the rear frame 3 with the acoustic panel 13, in the part of the race of this acoustic panel where the branch 29 and this panel are led to mutually interfering .
- the pads 31 are separated by a certain distance from the panel 13, since for the majority of the load cases there is no interference: the interference only occurs in certain load cases and only in direct jet position (ie for airplane maneuvers with strong relative displacements between structural elements).
- FIGS. 4 and 5 show a hollow zone 35 formed on the acoustic panel 13, at the right of the passage 19 allowing the positioning of the actuator 16, and the connection of the end of this actuator to a fixed plate 37 on the acoustic panel 13 downstream of the partition 15.
- recessed areas 35 of the acoustic panel 13 are areas in which the honeycomb structure (not shown) forming the acoustic panel 13, has a lower thickness and a higher density, thus giving this acoustic panel in this area, a higher resistance to compression forces.
- these plates 33 may be placed in these recessed zones 35, as can be seen in FIG. 5.
- This last arrangement has the advantage that the plates 33 do not constitute radial extra thickness with respect to the acoustic panel 13, thus contributing to the reduction of the radial thickness of the mobile structure 7.
- the rear frame 3 can be formed in particular composite material, and that in this case the pads 31 may be formed by folds of glass.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
- Special Spraying Apparatus (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Body Structure For Vehicles (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN200880112995.3A CN101835969B (zh) | 2007-10-25 | 2008-09-10 | 格栅式推力反向器 |
CA2702010A CA2702010A1 (fr) | 2007-10-25 | 2008-09-10 | Inverseur de poussee a grilles |
EP08851663A EP2209980A1 (fr) | 2007-10-25 | 2008-09-10 | Inverseur de poussee a grilles |
RU2010120236/06A RU2472960C2 (ru) | 2007-10-25 | 2008-09-10 | Реверсор тяги решетчатого типа и авиационная гондола, оборудованная таким реверсором тяги |
US12/739,344 US9140211B2 (en) | 2007-10-25 | 2008-09-10 | Cascade-type thrust reverser |
BRPI0818257 BRPI0818257A2 (pt) | 2007-10-25 | 2008-09-10 | Reversor de empuxo tipo cascata e nacela de avião |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR07/07501 | 2007-10-25 | ||
FR0707501A FR2922958B1 (fr) | 2007-10-25 | 2007-10-25 | Inverseur de poussee a grilles |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009066037A1 true WO2009066037A1 (fr) | 2009-05-28 |
Family
ID=39491381
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2008/001264 WO2009066037A1 (fr) | 2007-10-25 | 2008-09-10 | Inverseur de poussee a grilles |
Country Status (8)
Country | Link |
---|---|
US (1) | US9140211B2 (fr) |
EP (1) | EP2209980A1 (fr) |
CN (1) | CN101835969B (fr) |
BR (1) | BRPI0818257A2 (fr) |
CA (1) | CA2702010A1 (fr) |
FR (1) | FR2922958B1 (fr) |
RU (1) | RU2472960C2 (fr) |
WO (1) | WO2009066037A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102483011A (zh) * | 2009-08-14 | 2012-05-30 | 埃尔塞乐公司 | 推力反向装置 |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2965588B1 (fr) * | 2010-10-04 | 2015-05-01 | Aircelle Sa | Ensemble propulsif d'aeronef |
FR2978497B1 (fr) * | 2011-07-27 | 2013-08-16 | Aircelle Sa | Cadre arriere pour une structure d'inversion de poussee a grilles de deviation d'une nacelle de turboreacteur |
FR2994586B1 (fr) * | 2012-08-20 | 2014-08-08 | Aircelle Sa | Ensemble de poussee a grilles pour turboreacteur d'aeronef |
FR3007078B1 (fr) * | 2013-06-12 | 2015-06-05 | Aircelle Sa | Ferrure pour l'attache d'un verin d'un inverseur a portes d'une nacelle de turboreacteur et nacelle de turboreacteur |
FR3024753B1 (fr) * | 2014-08-11 | 2016-08-26 | Snecma | Ensemble de liaison pour parties de carter d'une turbomachine |
FR3031726B1 (fr) * | 2015-01-21 | 2017-02-24 | Aircelle Sa | Systeme pour la pose et la depose d’un ensemble propulsif sur un mat d’un aeronef |
US20180128206A1 (en) * | 2016-11-09 | 2018-05-10 | General Electric Company | Gas turbine engine |
FR3069891B1 (fr) * | 2017-08-07 | 2021-03-19 | Safran Nacelles | Grille d’inverseur de poussee pour nacelle d’aeronef |
RU2654531C1 (ru) * | 2017-09-29 | 2018-05-21 | Акционерное общество "ТВЭЛ" (АО "ТВЭЛ") | Тепловыделяющая сборка ядерного реактора |
FR3094757A1 (fr) * | 2019-04-04 | 2020-10-09 | Airbus Operations | Turboreacteur comportant une nacelle equipee d’un systeme inverseur et une grille de cascades mobile |
FR3122904B1 (fr) * | 2021-05-17 | 2023-04-28 | Safran Nacelles | Inverseur de poussée à grilles mobiles, comprenant une structure arrière de support de grilles intégrant une fonction acoustique |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0983939A1 (fr) * | 1998-09-03 | 2000-03-08 | Hispano-Suiza Aérostructures | Nacelle de turboréacteur à double flux à élément mobile mis à la masse |
US6170254B1 (en) * | 1998-12-18 | 2001-01-09 | Rohr, Inc. | Translating sleeve for cascade type thrust reversing system for fan gas turbine engine for an aircraft |
FR2804474A1 (fr) * | 2000-01-27 | 2001-08-03 | Hispano Suiza Sa | Inverseur de poussee a grilles aubagees de deviation a structure arriere fixe |
US20030019206A1 (en) * | 2001-07-24 | 2003-01-30 | Johnson Andrew T. | Thrust reverser position determination system and method |
Family Cites Families (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3241312A (en) * | 1963-09-18 | 1966-03-22 | Gen Electric | Thrust deflector |
US3241771A (en) * | 1963-09-18 | 1966-03-22 | Gen Electric | Thrust deflector and reverser |
US3241313A (en) * | 1963-09-18 | 1966-03-22 | Gen Electric | Thrust deflector |
US3248878A (en) * | 1963-09-18 | 1966-05-03 | Gen Electric | Thrust deflector and reverser |
US3281082A (en) * | 1963-10-16 | 1966-10-25 | Rolls Royce | Nozzles, e.g. deflecting jet discharge nozzles for jet propulsion engines |
US3292880A (en) * | 1964-09-01 | 1966-12-20 | Gen Electric | Thrust deflecting mechanism |
US3292864A (en) * | 1965-01-21 | 1966-12-20 | Gen Electric | Thrust reverser and deflector |
US3262270A (en) * | 1965-06-07 | 1966-07-26 | Gen Electric | Thrust reverser |
US3262271A (en) * | 1965-07-30 | 1966-07-26 | Gen Electric | Thrust reverser |
US3500645A (en) * | 1968-04-10 | 1970-03-17 | Rohr Corp | Thrust reverser |
US3717304A (en) * | 1970-05-06 | 1973-02-20 | Rolls Royce | Thrust reverser for fluid flow engine |
US3797785A (en) * | 1972-08-31 | 1974-03-19 | Rohr Industries Inc | Thrust modulating apparatus |
US4026105A (en) * | 1975-03-25 | 1977-05-31 | The Boeing Company | Jet engine thrust reverser |
US4193569A (en) * | 1976-02-12 | 1980-03-18 | Nichols William B | Process and apparatuses for landing aircraft on water covered landing surfaces |
US4458863A (en) * | 1980-03-10 | 1984-07-10 | The Boeing Company | Strut supported inlet |
FR2496766A1 (fr) * | 1980-12-23 | 1982-06-25 | Snecma | Dispositif de guidage de carenage mobile d'un systeme d'inversion de poussee |
US4778110A (en) * | 1982-09-30 | 1988-10-18 | Rohr Industries, Inc. | Modular composite cascade assembly |
US4596621A (en) * | 1984-01-03 | 1986-06-24 | The Boeing Company | Method of making a composite bond cascade for a thrust reverser unit of an aircraft engine nacelle |
GB2196911B (en) * | 1986-10-30 | 1990-03-14 | Rolls Royce Plc | Thrust reverser |
GB9014381D0 (en) * | 1990-06-28 | 1990-08-22 | Short Brothers Plc | A composite structural component |
US5313788A (en) * | 1991-08-07 | 1994-05-24 | General Electric Company | Thrust reversing arrangement for a long duct mixed flow exhaust turbofan engine |
GB2323065B (en) * | 1993-03-13 | 1998-12-09 | Rolls Royce Plc | Vectorable nozzle for aircraft |
FR2736390B1 (fr) * | 1995-07-05 | 1997-08-08 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a une coquille |
FR2758161B1 (fr) * | 1997-01-09 | 1999-02-05 | Hispano Suiza Sa | Inverseur de poussee a grilles a installation de verin de commande optimisee |
US5927647A (en) * | 1997-09-24 | 1999-07-27 | Rohr, Inc. | Blocker door frame pressure structure for translating cowl of cascade thrust reverser for aircraft jet engine |
US6311928B1 (en) * | 2000-01-05 | 2001-11-06 | Stage Iii Technologies, L.C. | Jet engine cascade thrust reverser for use with mixer/ejector noise suppressor |
FR2830051B1 (fr) * | 2001-09-27 | 2003-11-07 | Hurel Hispano Le Havre | Systeme de verrouillage sur un inverseur de poussee a grilles |
US6557799B1 (en) * | 2001-11-09 | 2003-05-06 | The Boeing Company | Acoustic treated thrust reverser bullnose fairing assembly |
US7146796B2 (en) * | 2003-09-05 | 2006-12-12 | The Nordam Group, Inc. | Nested latch thrust reverser |
US7264203B2 (en) * | 2003-10-02 | 2007-09-04 | The Nordam Group, Inc. | Spider actuated thrust reverser |
FR2872222B1 (fr) * | 2004-06-29 | 2006-08-25 | Hurel Hispano Sa | Procede d'ouverture d'un capot mobile equipant un inverseur de poussee |
US7093424B2 (en) * | 2004-08-24 | 2006-08-22 | Honeywell International, Inc. | Thrust reverser system electro-mechanical brake manual release mechanism |
US7409820B2 (en) * | 2004-11-16 | 2008-08-12 | Honeywell International Inc. | Electrical thrust reverser tertiary lock system including a voltage limiting circuit |
US7435180B2 (en) * | 2005-01-10 | 2008-10-14 | Honeywell International Inc. | Thrust reverser actuator system flex shaft assembly |
GB0606982D0 (en) * | 2006-04-07 | 2006-05-17 | Rolls Royce Plc | Aeroengine thrust reverser |
US20070237575A1 (en) * | 2006-04-11 | 2007-10-11 | Honeywell International, Inc. | Flexible shaft inline coupler |
-
2007
- 2007-10-25 FR FR0707501A patent/FR2922958B1/fr active Active
-
2008
- 2008-09-10 EP EP08851663A patent/EP2209980A1/fr not_active Withdrawn
- 2008-09-10 WO PCT/FR2008/001264 patent/WO2009066037A1/fr active Application Filing
- 2008-09-10 CN CN200880112995.3A patent/CN101835969B/zh active Active
- 2008-09-10 BR BRPI0818257 patent/BRPI0818257A2/pt not_active IP Right Cessation
- 2008-09-10 US US12/739,344 patent/US9140211B2/en active Active
- 2008-09-10 RU RU2010120236/06A patent/RU2472960C2/ru not_active IP Right Cessation
- 2008-09-10 CA CA2702010A patent/CA2702010A1/fr not_active Abandoned
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0983939A1 (fr) * | 1998-09-03 | 2000-03-08 | Hispano-Suiza Aérostructures | Nacelle de turboréacteur à double flux à élément mobile mis à la masse |
US6170254B1 (en) * | 1998-12-18 | 2001-01-09 | Rohr, Inc. | Translating sleeve for cascade type thrust reversing system for fan gas turbine engine for an aircraft |
FR2804474A1 (fr) * | 2000-01-27 | 2001-08-03 | Hispano Suiza Sa | Inverseur de poussee a grilles aubagees de deviation a structure arriere fixe |
US20030019206A1 (en) * | 2001-07-24 | 2003-01-30 | Johnson Andrew T. | Thrust reverser position determination system and method |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102483011A (zh) * | 2009-08-14 | 2012-05-30 | 埃尔塞乐公司 | 推力反向装置 |
Also Published As
Publication number | Publication date |
---|---|
US20100251693A1 (en) | 2010-10-07 |
RU2010120236A (ru) | 2011-11-27 |
RU2472960C2 (ru) | 2013-01-20 |
CA2702010A1 (fr) | 2009-05-28 |
CN101835969B (zh) | 2014-08-13 |
CN101835969A (zh) | 2010-09-15 |
US9140211B2 (en) | 2015-09-22 |
EP2209980A1 (fr) | 2010-07-28 |
FR2922958B1 (fr) | 2009-11-20 |
FR2922958A1 (fr) | 2009-05-01 |
BRPI0818257A2 (pt) | 2015-04-14 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2009066037A1 (fr) | Inverseur de poussee a grilles | |
EP2334557B1 (fr) | Dispositif de liaison entre une entree d'air et une motorisation d'une nacelle d'aeronef | |
EP2356028B1 (fr) | Trappe de surpression destinée à être montée sur une paroi d'une nacelle pour turboréacteur | |
EP2516271B1 (fr) | Nacelle incorporant un element de jonction entre une levre et un panneau d'attenuation acoustique | |
EP3247632B1 (fr) | Nacelle de turboréacteur d'aéronef | |
WO2013021110A1 (fr) | Dispositif d'inversion de poussée | |
EP2318679A1 (fr) | Paroi interne d'une nacelle de turbomachine | |
FR3087848A1 (fr) | Inverseur de poussee comprenant une membrane souple de deviation d'air | |
EP2742230A1 (fr) | Cône d'éjection pour turboréacteur d'aéronef | |
WO2009024655A1 (fr) | Fixation d'une structure d'une nacelle de turboreacteur par bride couteau/gorge renforcee | |
FR2649159A1 (fr) | Volets d'echappement | |
FR3083777A1 (fr) | Entree d'air, nacelle et ensemble propulsif d'aeronef a secteurs monoblocs | |
CA2829267A1 (fr) | Ensemble de joint d'etancheite anti-feu et nacelle comprenant un tel joint | |
EP3164588B1 (fr) | Cadre arrière pour une structure d'inverseur de poussée à grilles de déviation | |
FR2973467A1 (fr) | Dispositif d'etancheite destine a etre dispose entre deux structures d'une nacelle | |
WO2015028756A1 (fr) | Bras de servitude d'une nacelle de turboréacteur à double flux, comportant deux parties | |
FR3066788B1 (fr) | Moteur pour aeronef comprenant au moins un actionneur de systeme d'inversion de poussee agence dans un cone d'ejection des gaz | |
EP3877640B1 (fr) | Joint d'étanchéité pour nacelle de turboréacteur d'aéronef | |
FR2978731A1 (fr) | Nacelle d'aeronef incorporant un anneau de renfort. | |
EP2554480B1 (fr) | Dispositif de liaison plus particulièrement adapté pour assurer la liaison entre une entrée d'air et une motorisation d'une nacelle d'aéronef | |
EP4198294B1 (fr) | Inverseur de poussée à porte d'une nacelle de turboréacteur d aéronef à organe de déviation des fluides vers l extérieur | |
EP4173961B1 (fr) | Nacelle d aéronef comprenant une liaison entre des conduits comportant des collerettes orientées vers l' intérieur et aéronef comprenant au moins une telle nacelle | |
WO2023187298A1 (fr) | Ensemble propulsif pour aéronef comprenant un capot intermédiaire de type fixe démontable monté sur un système d'articulation | |
WO2023131761A1 (fr) | Inverseur de poussee comprenant des grilles fixes et une membrane d'obturation | |
WO2014170600A1 (fr) | Tuyère pour turbopropulseur d'aéronef à soufflante non carénée |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 200880112995.3 Country of ref document: CN |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 08851663 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2702010 Country of ref document: CA |
|
WWE | Wipo information: entry into national phase |
Ref document number: 12739344 Country of ref document: US |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
REEP | Request for entry into the european phase |
Ref document number: 2008851663 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2008851663 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2010120236 Country of ref document: RU |
|
ENP | Entry into the national phase |
Ref document number: PI0818257 Country of ref document: BR Kind code of ref document: A2 Effective date: 20100426 |