WO2009024659A1 - Inverseur de poussee avec systeme de freinage des actionneurs - Google Patents
Inverseur de poussee avec systeme de freinage des actionneurs Download PDFInfo
- Publication number
- WO2009024659A1 WO2009024659A1 PCT/FR2008/000845 FR2008000845W WO2009024659A1 WO 2009024659 A1 WO2009024659 A1 WO 2009024659A1 FR 2008000845 W FR2008000845 W FR 2008000845W WO 2009024659 A1 WO2009024659 A1 WO 2009024659A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- inverter
- braking means
- braking
- nacelle
- actuating means
- 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
- F02K1/54—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
Definitions
- the present invention relates to a thrust reverser with grids for turbojet nacelle
- the role of a thrust reverser during the landing of an aircraft is to improve the braking capacity of the latter 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. '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 movable hoods may furthermore fulfill a deflection function or simply the activation of other deflection means.
- the movable cowls slide along rails so that when backing up during the opening phase, they discover deflection blade grids disposed 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.
- these mobile covers are actuated by hydraulic or mechanical actuators with pneumatic or electric control.
- the two primary locks hold each mobile cowl in the retracted position and resume the efforts to translate said movable cowl. These locks are redundant to cover a possible failure of one of the primary locks, each lock being sized to fully resume the sum of efforts to translate the movable cover.
- the thrust reverser systems are provided with three separate control unlocking lines.
- the aerodynamic loads encountered in flight fatigue locks and further pushes are also exerted on the ground locks during maintenance operations when it is necessary to manually unlock these locks.
- the electrically operated thrust reverser systems are provided with helical link actuators, for example of the "ball screw” type, and are actuated by electric motors in direct contact with the actuator or by means of transmission cables. mechanical transmission. These rotary power transmission devices induce dimensional inertial loads for holding the actuator stops and the inverter structure and require the use of deceleration strategies of the electrical control in the end-of-travel zones.
- the present invention aims to provide a thrust reversal system generally more reliable and less subject to premature wear of some of its mechanical components.
- the present invention relates to a thrust reverser for a turbojet engine nacelle comprising at least one movable cowl mounted on a fixed inverter structure between a closed position in which they provide the aerodynamic continuity of the nacelle and deactivate means deflecting at least a portion of the air flow and an opening position in which they open a passage in the nacelle and activate said deflection means, each movable cover being able to be moved between these two positions by at least an actuating means, characterized in that the actuating means are associated with at least one mechanical braking means of said actuating means.
- the establishment of mechanical braking means of the mobile cover actuating means allows, on the one hand, to have additional security in the event of engine or electronic failure, but also to have a system of retaining the actuating means which can then be slightly claimed to meet the braking means.
- This last characteristic makes it possible to induce in the thrust reversal system a preload when the movable covers are in the closed position.
- this preload allows better absorption of vibrations and relative movements between parts, which reduces mechanical fatigue.
- the braking means contributes substantially to maintaining the inverter in the closed position.
- this preload makes it possible to reduce the tensions exerted on the means for locking the half-parts to one another, which makes it easier to unlock and reduces fatigue wear.
- the braking means may allow stop the system and avoid a violent arrival of mobile covers on the ultimate stops.
- the actuating means are electric actuating means of the electric cylinders type capable of being driven by at least one associated electric motor.
- the braking means are implemented at the level of the electric motor.
- the braking means are arranged to act at a drive shaft of the electric motor.
- the actuating means are driven through flexible transmission shafts.
- the braking means are arranged at the level of the flexible transmission shafts. More particularly, the brakes may be of jaw type coming to grip the drive shaft
- the inverter is a gate-type inverter.
- the braking means are associated with synchronization means between them.
- the braking means are static braking means having an engagement position by default current.
- the braking means are disengaged manually.
- the present invention also relates to a nacelle for a turbojet, characterized in that it comprises at least one thrust reverser according to the invention
- Figure 1 is a partial schematic perspective view of a nacelle incorporating a thrust reverser grids.
- Figure 2 is a schematic representation of the movable covers and their actuating system.
- Figure 3 is a schematic representation of the drive system of Figure 2.
- a thrust reverser 1 with grids generally has a structure comprising two semicircular movable hoods 2 slidable along rails (not shown) to discover deflection blade grids placed between the movable hoods 2 and a passage section. the airflow to deflect.
- Locking doors are arranged inside the structure so as to pivot and move from a position in which they do not interfere with the passage of the air flow 4 to a position in which they block this passage.
- these are mechanically connected to the movable cover 2 by hinges and to the fixed structure by a system of connecting rods.
- the displacement of the mobile covers 2 on the rails along the outside of the structure is provided by a set of jacks 6a, 6b mounted on a front frame inside which are housed an electric motor 7 and flexible transmission shafts. ⁇ a, ⁇ b respectively connected to the jacks 6a, 6b to actuate them.
- each movable cowl 2 can be translated along its rails under the action of three jacks 6a, 6b, comprising a central jack 6a and two additional jacks 6b, actuated by a single electric motor 7 connected to a control interface 9.
- the power delivered by the electric motor 7 is first distributed to the central cylinders 6a via two flexible transmission shafts ⁇ a, then to the additional cylinders 6b by flexible transmission shafts ⁇ b.
- each central cylinder 6a redistributing the movement to the additional cylinders 6b is equipped with a manual control box 9 allowing an opening or closing Manual of the corresponding mobile cover 2 during maintenance operations.
- the drive means of the two movable covers 2 are associated with braking means.
- Figures 2 and 3 show brake blocks 10 arranged on either side of the motor 7 at a drive shaft for the right cover and a drive shaft for the left cover.
- the braking means used may be, for example a static brake with a lack of current using a type of multi-disc brakes, spring-loaded and / or electrically unlockable by an integrated linear actuator.
- the brake is released and provides a precharge of the flexible transmission chain to avoid contact with the mechanical locks housed for example in the actuators
- the braking means 10 will be controlled on unlocking by one or more control units (not shown) when the thrust reversal is selected.
- the static brake can be used to immobilize the moving hoods 2 in emergencies and to avoid dynamic impacts in the event of loss of end-of-travel control.
- the brake holds the movable covers 2 on the stops and no longer on the lower locks. The unlocking of these can therefore be performed without load and therefore without wear on said locks.
- a manually operated brake inhibit mechanism is also installed.
- This mechanism can be a simple lever against the thrust of the springs, for example, and thus release the disks. Actuation of this lever will freely drive the movable covers 2 and then secure them in the desired position by re-engaging the brake.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Braking Arrangements (AREA)
- Wind Motors (AREA)
- Transmission Devices (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BRPI0813049-3A2A BRPI0813049A2 (pt) | 2007-08-20 | 2008-06-18 | "inversor de empuxo para nacela de motor a jato" |
CN200880102799A CN101784781A (zh) | 2007-08-20 | 2008-06-18 | 具有用于制动致动器的系统的推力反向器 |
EP08827585A EP2179164A1 (fr) | 2007-08-20 | 2008-06-18 | Inverseur de poussee avec systeme de freinage des actionneurs |
CA2696231A CA2696231A1 (fr) | 2007-08-20 | 2008-06-18 | Inverseur de poussee avec systeme de freinage des actionneurs |
US12/674,104 US20100212287A1 (en) | 2007-08-20 | 2008-06-18 | Thrust reverser with a system for braking the actuators |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0705901 | 2007-08-20 | ||
FR0705901A FR2920196B1 (fr) | 2007-08-20 | 2007-08-20 | Inverseur de poussee avec systeme de freinage des actionneurs |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009024659A1 true WO2009024659A1 (fr) | 2009-02-26 |
Family
ID=39229028
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2008/000845 WO2009024659A1 (fr) | 2007-08-20 | 2008-06-18 | Inverseur de poussee avec systeme de freinage des actionneurs |
Country Status (8)
Country | Link |
---|---|
US (1) | US20100212287A1 (fr) |
EP (1) | EP2179164A1 (fr) |
CN (1) | CN101784781A (fr) |
BR (1) | BRPI0813049A2 (fr) |
CA (1) | CA2696231A1 (fr) |
FR (1) | FR2920196B1 (fr) |
RU (1) | RU2010109787A (fr) |
WO (1) | WO2009024659A1 (fr) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2959488B1 (fr) * | 2010-04-28 | 2012-05-18 | Aircelle Sa | Nacelle pour moteur d'aeronef a inverseur de poussee a grilles et a tuyere adaptative |
CN102254631B (zh) * | 2011-05-17 | 2012-11-21 | 芜湖飞云电工机械有限公司 | 一种线缆设备的制动装置 |
FR2990248B1 (fr) * | 2012-05-04 | 2015-09-25 | Aircelle Sa | Systeme de commande pour inverseur de poussee |
GB2510635B (en) * | 2013-02-12 | 2017-11-01 | Ge Aviat Systems Ltd | Method for predicting faults in an aircraft thrust reverser system |
FR3028295B1 (fr) * | 2014-11-06 | 2020-01-17 | Safran Electronics & Defense | Systeme d'actionnement d'une structure mobile d'un inverseur de poussee d'un aeronef, inverseur de poussee et reacteur comprenant un tel systeme. |
US10309343B2 (en) * | 2014-11-06 | 2019-06-04 | Rohr, Inc. | Split sleeve hidden door thrust reverser |
US10613727B2 (en) | 2016-02-19 | 2020-04-07 | Ppg Industries Ohio, Inc. | Color and texture match ratings for optimal match selection |
CN109311538B (zh) * | 2016-06-14 | 2022-06-03 | 加拿大空客有限合伙公司 | 用于致动飞行器整流罩的系统和方法 |
FR3063585B1 (fr) * | 2017-03-06 | 2019-04-05 | Safran Electronics & Defense | Dispositif d’actionnement a deux actionneurs |
CN109026436A (zh) * | 2018-08-22 | 2018-12-18 | 中国商用飞机有限责任公司 | 反推作动装置及涡轮喷气发动机短舱 |
FR3093993B1 (fr) * | 2019-03-21 | 2021-02-26 | Safran Aircraft Engines | Procédé de contrôle du freinage des roues d’un avion et contrôleur de freinage de roues associé |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20030159429A1 (en) * | 2002-02-27 | 2003-08-28 | Langston Todd A. | Gearless electric thrust reverser actuators and actuation system incorporating same |
US6666307B1 (en) * | 2002-08-05 | 2003-12-23 | Honeywell International, Inc. | Thrust reverser system with a pass-through torque activated brake |
US20060042229A1 (en) * | 2004-08-24 | 2006-03-02 | Casey Hanlon | Thrust reverser system electro-mechanical brake manual release mechanism |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5228641A (en) * | 1991-08-15 | 1993-07-20 | Rohr, Inc. | Cascade type aircraft engine thrust reverser with hidden link actuator |
GB2305460B (en) * | 1995-09-25 | 1999-12-15 | Dowty Boulton Paul Ltd | Lock for engine thrust reverser |
US6125975A (en) * | 1998-11-17 | 2000-10-03 | Inertia Dynamics | Sealed electromagnetic brake |
US7409820B2 (en) * | 2004-11-16 | 2008-08-12 | Honeywell International Inc. | Electrical thrust reverser tertiary lock system including a voltage limiting circuit |
-
2007
- 2007-08-20 FR FR0705901A patent/FR2920196B1/fr active Active
-
2008
- 2008-06-18 US US12/674,104 patent/US20100212287A1/en not_active Abandoned
- 2008-06-18 CA CA2696231A patent/CA2696231A1/fr not_active Abandoned
- 2008-06-18 BR BRPI0813049-3A2A patent/BRPI0813049A2/pt not_active IP Right Cessation
- 2008-06-18 RU RU2010109787/06A patent/RU2010109787A/ru unknown
- 2008-06-18 WO PCT/FR2008/000845 patent/WO2009024659A1/fr active Application Filing
- 2008-06-18 EP EP08827585A patent/EP2179164A1/fr not_active Withdrawn
- 2008-06-18 CN CN200880102799A patent/CN101784781A/zh active Pending
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20030159429A1 (en) * | 2002-02-27 | 2003-08-28 | Langston Todd A. | Gearless electric thrust reverser actuators and actuation system incorporating same |
US6666307B1 (en) * | 2002-08-05 | 2003-12-23 | Honeywell International, Inc. | Thrust reverser system with a pass-through torque activated brake |
US20060042229A1 (en) * | 2004-08-24 | 2006-03-02 | Casey Hanlon | Thrust reverser system electro-mechanical brake manual release mechanism |
Also Published As
Publication number | Publication date |
---|---|
BRPI0813049A2 (pt) | 2014-12-16 |
EP2179164A1 (fr) | 2010-04-28 |
CA2696231A1 (fr) | 2009-02-26 |
FR2920196A1 (fr) | 2009-02-27 |
CN101784781A (zh) | 2010-07-21 |
US20100212287A1 (en) | 2010-08-26 |
FR2920196B1 (fr) | 2013-08-09 |
RU2010109787A (ru) | 2011-09-27 |
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