EP2932077A1 - Inverseur de poussée de nacelle et nacelle équipée d'au moins un inverseur - Google Patents
Inverseur de poussée de nacelle et nacelle équipée d'au moins un inverseurInfo
- Publication number
- EP2932077A1 EP2932077A1 EP13818282.9A EP13818282A EP2932077A1 EP 2932077 A1 EP2932077 A1 EP 2932077A1 EP 13818282 A EP13818282 A EP 13818282A EP 2932077 A1 EP2932077 A1 EP 2932077A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- thrust reverser
- outer cover
- downstream frame
- nacelle
- frame
- Prior art date
- Legal status (The legal status 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 status listed.)
- Withdrawn
Links
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 10
- 210000002816 gill Anatomy 0.000 claims description 2
- 239000000725 suspension Substances 0.000 claims description 2
- 238000000926 separation method Methods 0.000 claims 1
- 210000003462 vein Anatomy 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 102100033121 Transcription factor 21 Human genes 0.000 description 1
- 101710119687 Transcription factor 21 Proteins 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/08—Inspection panels for power plants
-
- 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
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/76—Control or regulation of thrust reversers
- F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/72—Maintenance
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
Definitions
- the present invention relates to a thrust reverser for a turbojet engine nacelle, as well as a nacelle for a turbojet engine incorporating a thrust reverser, according to the invention.
- each engine is housed in a nacelle serving as both support and engine cover.
- this boat is reliquely connected to it or via a mast, either at the wing or the fuselage of the aircraft.
- the nacelle can also receive different mechanical systems annexes, including a mechanical thrust reverser actuation system.
- the thrust reverser is a device that directs the airflow generated by the turbojet engine to the front, allowing both to shorten the landing distance and also to limit the stress of the brakes at the undercarriages.
- a nacelle has a substantially tubular structure, with an air inlet upstream of the turbojet, followed by a median section intended to surround a turbojet fan, a downstream section integrating both the inversion means of thrust and surrounding the combustion chamber of the turbojet engine.
- the nacelle further comprises, at its downstream end, a nozzle for ejecting the flow coming out of the turbojet engine.
- turbofan engines in these turbojets, it is generated by means of the blades of the fan, both a hot air flow called primary flow, and a cold air flow called secondary flow.
- This second flow of cold air circulates outside the turbojet through an annular passage also called vein, this vein being formed between a fairing of the turbojet engine and the inner wall of the nacelle.
- the thrust reverser completely or partially obstruct the flow of cold air flow, to redirect this flow to the front of the nacelle.
- the inversion is performed by translating the outer cover with the grids that come out of their housing and allow the redirection of airflow forward.
- the present invention falls into this category of thrust reverser with movable grids.
- nacelle structures there are also two main types of nacelle structures, namely a first type in which the outer cover is formed with two half-covers, of substantially semi-cylindrical shape, these two half-covers being articulated in the upper part on hinges. substantially parallel to the direction of translation of the outer cover.
- connection between the two half-covers is made by locks arranged in the lower part.
- a second type of structure of the nacelle is said monoblock structure or O-structure in which the outer cover is formed of a single cylindrical part.
- the present invention is in the field of nacelles of the first mentioned category, commonly called D-structure platform.
- the present invention is an improvement to the D-frame pods, and mobile grid thrust reverser.
- any type of nacelle maintenance operations are to be provided regularly and to do this, it is necessary to access the interior of the nacelle and, for example to the turbojet engine, or to the ancillary devices including the structure internal of the inverter.
- the access to the interior of the nacelle is achieved by unlocking the two half-covers allowing a "butterfly" opening, after having previously made a unlocking the movable grilles and the half covers.
- this double unlocking is particularly disadvantageous, on the one hand the disconnection of the mobile grids is made complicated by restricted access to the disconnection system, and, on the other hand, this double unlocking system detrimentally increases the weight of the nacelle; finally this double unlocking system also increases the dimensions of the nacelle and the associated cover.
- An object of the present invention is to overcome the aforementioned drawbacks by providing a nacelle with a thrust reverser in which access to the engine is authorized by a single manual unlocking action.
- Another object of the present invention is to provide a nacelle in which access to the motor can be carried out indifferently when the outer cover is translated backwards, corresponding to the indirect jet position or to the front corresponding to the direct jet position .
- Another object of the present invention is to provide a nacelle in which access to the motor can be achieved when the fan cowl is fixed or closed.
- Another object of the present invention is to provide a nacelle whose weight and dimensions are improved compared to the D-shaped platform, with inverter movable gates, conventionally used until now.
- the invention relates to a thrust reverser for a turbojet engine nacelle, comprising:
- At least one outer cover made in two hinged covers hinged on hinges, movable in translation from a so-called closing position to at least one open position
- Thrust reversal means comprising at least deflection grids supported at their upstream ends by an upstream frame, and at their downstream end by a downstream frame, and enclosed in a casing formed by a fan casing and by a blower hood,
- the invention also relates to a nacelle or aircraft turbojet, comprising at least one thrust reverser according to the invention.
- FIG. 1 shows a schematic perspective view of a turbojet engine nacelle made according to the invention in a maintenance position
- FIG. 2 is a sectional view of the nacelle shown in Figure 1 and centered on the median part of the nacelle at the mobile gates;
- FIG. 3 is a sectional view of the nacelle as shown in Figure 2, the nacelle being deposited in reverse jet;
- FIG. 4 represents an enlarged view of the embodiment detail denoted I in FIG. 2,
- FIG. 5 shows, in a perspective view, the connection means in the disconnected position.
- FIG. 1 showing a nacelle 1 turbojet (not shown), arranged in maintenance configuration with an outer cover 2 made with two half-covers 3, connected to the upper part of the nacelle 4, this upper part 4 being intended to serve as a link interface with a reactor mast not shown in the accompanying drawings.
- the downstream frame can translate backwards by means of the first actuating means 8 connected thereto.
- the outer cover 2 can translate backwards, and also when the outer cover 2 is unlocked, second actuating means 9 allow a rotational movement of each half-cover 3.
- This figure 1 also shows the fan 10 and the fan cover 1 1.
- FIG. 2 shows more in detail different parts of the nacelle 1, and in particular a thrust reverser 12, said nacelle 1 being in the direct jet position in Figure 2, and reverse jet position in Figure 3.
- the thrust reverser 12 comprises reversing means 13, with deflection grids 14.
- deflection grids 14 are supported at their upstream end 15 by an upstream frame 16 and at their downstream end 17 by a downstream frame 18.
- the upstream frame 16 simply ensures the connection of the deflection grids 14 between them.
- these deflection gratings 14 are closed in an envelope 19 formed by the fan casing 20 and the fan casing 11.
- the thrust reversal means 1 3 further comprise connecting means 21 between the downstream frame 18 and the outer cover 2.
- the connecting means 21 make it possible to maintain the connection between the outer cover 2 and the downstream frame 18, upon actuation of the first actuating means 8.
- FIG. 3 thus shows that the first actuating means
- the connecting means 21 comprise a groove 23 cooperating with a knife 24.
- the groove 23 is integral with the downstream frame 18, while the knife 24 is secured to the outer cover 2 via the interplanar frame 22.
- the groove 23 could be solitary of the outer cover 2, while the knife 24 would be secured to the downstream frame 18.
- the drive is effected of the same that is to say that the deflection grids 14 and the downstream frame 1 8 are driven forwardly in direction of the hood of the fan 1 1 inside their envelope 19., moving by the same the groove 23 which cooperates with the knife 24 and reposition the outer cover 2 to its initial position.
- the two half-covers 3 are partially raised allowing access to the turbojet engine and, furthermore, it can be seen that the deflection grids 14 and the downstream frame 18 are not visible. more connected to the external cover 2. To do this, the operator actuates the second actuating means 9, after having previously unlocked half-covers 3 from the locking / unlocking means 7.
- Unlocking the half-covers 3 allows the latter to pivot about the axis formed by their respective hinges 5.
- the second actuating means 9 allow the rotation of each half-cover 3, ie their raising for the access operations inside the platform 1 or when the maintenance operations are performed, their lowering in to achieve again locking the half-covers 3 between them.
- the second rotation actuating means 9 comprise opening control cylinders 31, these control cylinders 31 being, on the one hand, attached on one side to either the deflection gratings 14, or in one variant of the downstream frame 18, and secondly, on the other side, to an integral element of the outer cover 2.
- the rotation of the half-covers 3 can be performed manually.
- a locking rod will be extended and locked manually to maintain the assembly in the open position.
- connection means 21 in the disconnected position, it is understood that when the outer cover 2 or more exactly when the half-covers 3 are rotated, the knife 24, ideal floor of the hood outer, also rotates and the knife head 24 out of the groove 23.
- This structure of the connecting means 21 is therefore particularly advantageous with respect to the existing solutions in the fields of D-type mobile grid-type nacelles, since it ensures both a reliable drive in translation between the deflection gates 14 and the hood external 2, while ensuring a disconnection between these elements, when the second actuating means 9 come up the half-covers 3.
- Another advantage of this structure is that the disengagement of the knife 24 with respect to the groove 23 can be achieved regardless of the position of the outer cover 2 relative to the casing of the fan 20, that is to say when the nacelle 1 is in the direct jet position, inverted jet or for any intermediate position between these two extreme positions.
- the groove 23 is connected to a joining piece 25.
- This joining piece 25 is intended to ensure aerodynamic continuity with the deflection edge 26 of the fan casing 20.
- this connecting piece 25 which preferably has a substantially V-shaped profile, also bears, on its inner face 27, a seal 28.
- This seal 28 is in contact with the deflection edge 26 of the fan casing, preventing the creation of a secondary flow between the fan casing and the front of the flaps, when the pod 1 is in the direct jet position.
- the seal 28 comprises a base 29 secured to the joining piece 25, as well as a hollow tubular portion 30 coming into contact with the deflection edge 26, the hollow tubular portion 30 allowing the joint to be crushed. on the wall of the deflection edge 26, thereby improving the sealing of this zone.
- the deflection grids 14 at one end of the deflection grids 14 a cooperation with the engine mast of the nacelle.
- the end of the grid 14 allows a sliding of the grid along the latter to collaborate with a motor suspension positioned at deflection gilles 14. This cooperation is obtained, advantageously, using a rail in U allowing the recovery of the vertical forces applied to said end of the grids.
- a nacelle 1 equipped with a thrust reverser 12, in which it is not necessary to have the security and locking elements between the deflection grids 14 and other sets fixed nacelle 1, allowing easy access to the engine, a weight and a reduced volume for the nacelle 1, while reliably ensuring the passage of direct jet reverse jet and vice versa.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1261918A FR2999239B1 (fr) | 2012-12-12 | 2012-12-12 | Inverseur de poussee de nacelle et nacelle equipee d'au moins un inverseur |
PCT/FR2013/053014 WO2014091140A1 (fr) | 2012-12-12 | 2013-12-10 | Inverseur de poussée de nacelle et nacelle équipée d'au moins un inverseur |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2932077A1 true EP2932077A1 (fr) | 2015-10-21 |
Family
ID=47902132
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13818282.9A Withdrawn EP2932077A1 (fr) | 2012-12-12 | 2013-12-10 | Inverseur de poussée de nacelle et nacelle équipée d'au moins un inverseur |
Country Status (7)
Country | Link |
---|---|
US (1) | US9677502B2 (fr) |
EP (1) | EP2932077A1 (fr) |
CN (1) | CN104854335B (fr) |
CA (1) | CA2893633A1 (fr) |
FR (1) | FR2999239B1 (fr) |
RU (1) | RU2015128041A (fr) |
WO (1) | WO2014091140A1 (fr) |
Families Citing this family (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3023325B1 (fr) * | 2014-07-04 | 2016-07-15 | Aircelle Sa | Cadre arriere pour une structure d'inverseur de poussee a grilles de deviation |
FR3031725B1 (fr) * | 2015-01-21 | 2018-06-01 | Safran Nacelles | Nacelle de turboreacteur d’aeronef |
US10514004B2 (en) * | 2015-12-14 | 2019-12-24 | Rohr, Inc. | Cascade assembly for a thrust reverser of an aircraft nacelle |
PL415487A1 (pl) * | 2015-12-31 | 2017-07-03 | General Electric Company | Formowana kompozytowa osłona chroniąca przed zużyciem krawędzi dla złącza w postaci wpustu V-kształtnego i łopatki V-kształtnej |
US10428764B2 (en) | 2016-02-10 | 2019-10-01 | Rohr, Inc. | Deflection limiter for a cascade assembly of a thrust reverser |
US20180023509A1 (en) * | 2016-07-25 | 2018-01-25 | United Technologies Corporation | Thrust reverser structure mounted to fan case |
FR3063532B1 (fr) * | 2017-03-06 | 2019-04-05 | Safran Electronics & Defense | Actionneur equipe d’un systeme de no back a zone d’inhibition |
FR3064307B1 (fr) * | 2017-03-22 | 2019-03-29 | Airbus Operations | Nacelle d'un turboreacteur comportant un volet inverseur |
US10640223B2 (en) | 2017-08-22 | 2020-05-05 | Rohr, Inc. | Safety maintenance panel for a thrust reverser |
FR3073572B1 (fr) | 2017-11-16 | 2020-10-02 | Safran Nacelles | Inverseur de poussee a grilles mobiles pour ensemble propulsif d’aeronef et procedes de montage et demontage s’y rapportant |
FR3074855A1 (fr) * | 2017-12-11 | 2019-06-14 | Airbus Operations | Grille pour la formation d'un flux d'inversion d'un turboreacteur d'aeronef |
FR3075760B1 (fr) * | 2017-12-21 | 2020-01-31 | Safran Nacelles | Nacelle de moteur d’aeronef |
FR3076865B1 (fr) | 2018-01-18 | 2020-01-03 | Safran Nacelles | Ensemble arriere d'une nacelle de turboreacteur d'aeronef comprenant un inverseur de poussee a grilles coulissantes |
FR3078998B1 (fr) * | 2018-03-19 | 2020-03-06 | Safran Aircraft Engines | Ensemble propulsif a double flux, comprenant un inverseur de poussee a grilles mobiles |
FR3094698B1 (fr) * | 2019-04-02 | 2022-09-09 | Safran Aircraft Engines | Manche d’entree d’air pour une nacelle d’un ensemble propulsif d’aeronef |
FR3096741B1 (fr) * | 2019-05-28 | 2022-11-18 | Safran Nacelles | Ensemble propulsif d’aéronef |
FR3099221B1 (fr) * | 2019-07-22 | 2022-08-26 | Safran Nacelles | Joint d’étanchéité pour aéronef |
CN113864079B (zh) * | 2020-06-30 | 2022-07-12 | 中国航发商用航空发动机有限责任公司 | 反推力装置和航空发动机 |
FR3119648B1 (fr) | 2021-02-05 | 2023-01-27 | Safran Nacelles | Inverseur de poussée comprenant des grilles et des capots mobiles assemblés par embrèvement |
FR3121713B1 (fr) | 2021-04-13 | 2023-11-24 | Safran Nacelles | Inverseur de poussée à grilles mobiles comprenant une structure fixe plurifonctionnelle |
FR3122905A1 (fr) | 2021-05-14 | 2022-11-18 | Safran Nacelles | Ensemble propulsif d’aéronef comprenant un actionneur relié à un bras structural tel qu’une aube directrice de sortie |
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 |
FR3126452A1 (fr) | 2021-08-25 | 2023-03-03 | Safran Nacelles | Inverseur à grilles mobiles pour ensemble propulsif d’aéronef, comprenant un système pour limiter le flambage d’un actionneur de l’inverseur |
FR3127479B1 (fr) | 2021-09-24 | 2023-09-01 | Safran Nacelles | Nacelle pour ensemble propulsif d’aéronef, comprenant un inverseur de poussée à grilles mobiles, et de préférence au moins un capot de soufflante pivotant |
FR3131757B1 (fr) | 2022-01-10 | 2023-11-24 | Safran Nacelles | Inverseur de poussee comprenant des grilles mobiles et une membrane d’obturation |
FR3132545A1 (fr) | 2022-02-04 | 2023-08-11 | Safran Nacelles | Ensemble propulsif pour aeronef comprenant un inverseur de poussee a grilles mobiles et a actionneur monte de maniere optimisee |
FR3141969A1 (fr) * | 2022-11-16 | 2024-05-17 | Safran Nacelles | Inverseur de poussee comprenant une membrane d’obturation equipee d’un joint d’etancheite |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1386232A (en) * | 1971-03-31 | 1975-03-05 | Short Brothers & Harland Ltd | Fluid propulsion systems |
US5864922A (en) * | 1996-08-08 | 1999-02-02 | The Boeing Company | Self centering hinge |
FR2756323B1 (fr) * | 1996-11-28 | 1998-12-31 | Hispano Suiza Sa | Dispositif de liaison d'un inverseur de poussee a un turbomoteur |
FR2897339B1 (fr) * | 2006-02-16 | 2008-04-11 | Aircelle Sa | Nacelle de turboreacteur a ouverture laterale des capots |
FR2905357B1 (fr) * | 2006-08-31 | 2009-07-03 | Aircelle Sa | Systeme de verrouillage pour capot mobile de nacelle |
FR2914700B1 (fr) * | 2007-04-04 | 2009-05-22 | Aircelle Sa | Inverseur de poussee pour moteur a reaction |
FR2920141B1 (fr) * | 2007-08-20 | 2009-10-30 | Aircelle Sa | Nacelle de turboreacteur, destinee a equiper un aeronef |
FR2953490B1 (fr) * | 2009-12-07 | 2012-02-24 | Aircelle Sa | Ensemble arriere de nacelle pour turboreacteur |
US8875486B2 (en) * | 2010-05-17 | 2014-11-04 | Rohr, Inc. | Guide system for nacelle assembly |
US9783315B2 (en) * | 2012-02-24 | 2017-10-10 | Rohr, Inc. | Nacelle with longitudinal translating cowling and rotatable sleeves |
-
2012
- 2012-12-12 FR FR1261918A patent/FR2999239B1/fr active Active
-
2013
- 2013-12-10 RU RU2015128041A patent/RU2015128041A/ru not_active Application Discontinuation
- 2013-12-10 CA CA2893633A patent/CA2893633A1/fr not_active Abandoned
- 2013-12-10 EP EP13818282.9A patent/EP2932077A1/fr not_active Withdrawn
- 2013-12-10 CN CN201380065045.0A patent/CN104854335B/zh not_active Expired - Fee Related
- 2013-12-10 WO PCT/FR2013/053014 patent/WO2014091140A1/fr active Application Filing
-
2015
- 2015-05-22 US US14/720,403 patent/US9677502B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR2999239B1 (fr) | 2015-02-20 |
CN104854335A (zh) | 2015-08-19 |
US20150260126A1 (en) | 2015-09-17 |
CA2893633A1 (fr) | 2014-06-19 |
FR2999239A1 (fr) | 2014-06-13 |
US9677502B2 (en) | 2017-06-13 |
CN104854335B (zh) | 2016-04-13 |
WO2014091140A1 (fr) | 2014-06-19 |
RU2015128041A (ru) | 2017-01-16 |
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