Classifications

• • E—FIXED CONSTRUCTIONS
  • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
  • E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
  • E05C19/00—Other devices specially designed for securing wings, e.g. with suction cups
  • E05C19/10—Hook fastenings; Fastenings in which a link engages a fixed hook-like member
• • 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
  • B64D29/06—Attaching of nacelles, fairings or cowlings
• • 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
• • 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
  • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
• • 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
  • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/0206—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
• • 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
  • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/0266—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
  • B64D2033/0286—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
• • E—FIXED CONSTRUCTIONS
  • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
  • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
  • E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
  • E05B47/0001—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof
  • E05B2047/0014—Constructional features of actuators or power transmissions therefor
  • E05B2047/0018—Details of actuator transmissions
  • E05B2047/0023—Nuts or nut-like elements moving along a driven threaded axle
• • E—FIXED CONSTRUCTIONS
  • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
  • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
  • E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
  • E05B2047/0084—Key or electric means; Emergency release
  • E05B2047/0086—Emergency release, e.g. key or electromagnet
• • E—FIXED CONSTRUCTIONS
  • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
  • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
  • E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
  • E05B47/0001—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof
  • E05B47/0012—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof with rotary electromotors
• • 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
  • F05D2230/70—Disassembly methods

Definitions

• the present invention relates to a locking device for a translatable air intake structure equipping a turbojet engine nacelle.
• An aircraft is propelled by one or more propulsion units comprising a turbojet engine housed in a tubular nacelle.
• Each propulsion unit is attached to the aircraft by a mast located generally under a wing or at the fuselage.
• a nacelle generally has a structure comprising an air inlet upstream of the engine, a median section intended to surround a fan of the turbojet engine, and a downstream section intended to surround the combustion chamber of the turbojet engine and housing thrust reverser means. .
• the air intake comprises, on the one hand, an inlet lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet engine, and other on the other hand, a downstream structure to which the lip is attached and intended to properly channel the air towards the blades of the fan, said downstream structure comprising an outer shell and an internal acoustic panel.
• the assembly is attached upstream of a fan casing belonging to the median section of the nacelle.
• the median structure surrounds the blower and is generally broken down into an inner wall forming said blower housing and an outer wall in the form of removable hoods pivotally mounted about a longitudinal hinge axis at the top (at
• This solution consists in integrating the air intake lip to the outer shell by including all or part of the cover surrounding the fan casing so as to form a one-piece structure.
• the entire wall thus formed is movably mounted in translation.
• the inner edge of the air intake lip comes, when said translatable structure is in the closed position, in contact with an upstream zone of an internal wall of the structure of the engine.
• air inlet, inner wall generally made in the form of an acoustic panel.
• the translatable structure is guided and held on a fixed structure, including the inner wall of the air inlet structure, by a plurality of rails.
• the interface is sealed by a seal system and is reinforced by a system of centering pins disposed on the periphery of the air intake lip / acoustic shroud junction and to improve its resistance to radial displacements.
• the maintenance of the mobile structure in the longitudinal directions is mainly by bolting the mobile structure on a fixed structure in an area close to an installation interface of the acoustic shroud on the fan casing.
• Such a locking system therefore requires a large number of fastening means whose assembly and disassembly are long and tedious.
• a manual locking system comprising a gripping system of the mobile structure by the handle at the end of maneuvering the structure. This technique avoids a long and tedious assembly / disassembly with a system of maintenance by bolting.
• a system is not suitable for a motorized drive of the mobile structure since the manual drive system and the lock are coupled. It will also be noted that the adjustment of the pretension of the locks is also long and tedious. Therefore, there is a need for a locking system of such a mobile structure to solve all or part of these problems.
• the present invention relates to a turbojet engine nacelle comprising an air intake structure adapted to channel a flow of air to a fan of the turbojet engine and a median structure intended to surround said fan and to which is attached the air intake structure to provide aerodynamic continuity
• the air inlet structure comprising, on the one hand, at least one inner panel attached to the middle structure and forming therewith a fixed structure of the nacelle, and secondly, at least one longitudinal outer panel removably attached to the fixed structure and incorporating an air inlet lip so as to form a removable air inlet structure, characterized in that that the removable air inlet structure is equipped with peripheral locking means comprising at least one electric lock each adapted to cooperate with a complementary retaining means.
• the locking and unlocking of the air intake structure are easily controllable and remotely operable by means of one or more centralized controls, for example an airplane control and / or a nacelle control.
• electrical locking means also avoids the establishment of manual locking and unlocking means (handles, cables) generating aerodynamic accidents while also avoiding the use of bolting systems whose implementation in place and unlocking are long and tedious.
• the electric lock comprises a hook capable of cooperating with a corresponding stirrup.
• the removable air intake structure is equipped with a rail / slide type guide system mounted on a part of the fixed structure.
• the electric lock or locks are each arranged substantially at a guide rail.
• the locking means are preferably located at the level of the zones of effort and therefore allow a better recovery of the latter.
• the electric lock or locks are associated with at least one means for detecting the locking and / or unlocking position.
• the nacelle comprises a control member of the locking means.
• control member is a handle, preferably retractable, adapted to allow the driving of the moving air inlet structure.
• each electrical locking means is adapted to be locked and unlocked manually from outside the nacelle, for example by means of a hatch arranged in the outer wall of the air intake structure.
• the electrical locking means are able to receive each a mechanical inhibition pin designed to allow the locking of the corresponding electrical locking means.
• the complementary retaining means of each locking means are adjustable in pretension.
• the adjustment of the complementary retaining means is effected by means of a set screw capable of moving a bead having an inclined surface so as to allow adjustment of the complementary retaining means in the direction of restraint. .
• the adjustment of the complementary retaining means is effected by means of an endless screw adapted to cooperate with a threaded zone of said retaining means so as to allow a translation of the retaining means in the direction of detention.
• the adjustment of the complementary retaining means can be carried out from outside the nacelle.
• the complementary retaining means are attached to the fixed structure while the electric locks are attached to the removable structure.
• Figure 1 is a partial schematic representation of an air intake structure of a nacelle according to the invention, the air inlet structure being in the closed position.
• Figure 2 is a partial schematic representation of the air intake structure of Figure 1, the air inlet structure being in the open position.
• Figure 3 is an enlarged partial schematic representation of a first embodiment of a locking means equipping the nacelle of Figures 1 and 2.
• Figure 4 is an enlarged partial schematic representation of a second embodiment of a locking means equipping the nacelle of Figures 1 and 2.
• FIG. 5 is an enlarged partial schematic representation of a third embodiment of a locking means equipping the nacelle of FIGS. 1 and 2.
• FIG. 6 is an enlarged partial schematic representation of a locking means equipping the nacelle with Figures 1 and 2, said locking means being mechanically inhibited.
• FIG. 7 represents a first embodiment of the pretensioning of a locking means equipping a nacelle according to the invention.
• FIG. 8 represents a second embodiment of the pretensioning of a locking means equipping a nacelle according to the invention.
• a nacelle according to the invention as partially shown in FIGS. 1 and 2 constitutes a tubular housing for a turbojet engine
• turbojet (not visible) which it serves to channel the air flows it generates by defining internal and external aerodynamic lines necessary to obtain optimal performance. It also houses various components necessary for the operation of the turbojet as well as ancillary systems such as a thrust reverser.
• the nacelle is intended to be attached to a fixed structure of an aircraft, such as a wing, through a pylon.
• the nacelle has a structure comprising a front section forming an air inlet 2, a middle section (not visible) surrounding a blower (not visible) of the turbojet, and a rear section
• turbojet (Not visible) surrounding the turbojet and can house a thrust reversal system (not shown).
• the air intake 2 is divided into two zones, namely on the one hand, an inlet lip 2a adapted to allow optimal capture to the turbojet of the air necessary to supply the fan and compressors internal turbojet, and secondly, a downstream structure 2b comprising an outer panel 20 and an inner panel 21, generally acoustic.
• the lip 2a is integrated with the outer panel 20 so as to form a single piece that can be dismantled, the inner panel 21 being attached upstream of a casing of the blower. belonging to the median section of the nacelle via fastening flanges 3, integral respectively with the downstream structure 2b and the housing.
• the air intake structure 2 may be modular and include a plurality of outer panels 20 each defining a corresponding air inlet lip portion 2a.
• the inner panel 21 is made from an acoustic shell and is connected through the flanges 3 to the casing of the middle section. This inner panel 21 therefore constitutes a fixed part of the air inlet structure 2 on which is intended to be mounted and removably fixed, the outer panel 20 incorporating the air inlet lip 2a.
• outer panel 20 may also comprise all or part of an outer panel of the median structure.
• each flange 3 also supports a radial peripheral wall 5.
• This partition 5 may carry centering and secondary centering extending perpendicular to said partition 5 upstream of the nacelle.
• the air intake structure 2 can extend axially through its outer panel 20 beyond a fastening flange of the inner panel 21 to the fixed structure of the platform 1 to neighboring an external structure of a thrust reversal structure belonging to the downstream section of the nacelle and possibly covering the covers.
• a lock system can then be provided to maintain the air intake structure on the partition 5 integral with the housing structure or an upstream structure of the downstream structure.
• air 2a forms, in accordance with the state of the art, a removable part intended to be reported on the fixed part and more particularly on the peripheral wall 5.
• the removable structure may be mounted, for example, on a slide rail system 6 / slide 7 comprising a plurality of rails 6 / slides 7 distributed on the periphery of the air inlet structure 2.
• the maintenance of the removable structure is effected by locking means comprising at least one electric lock 10 of the hook type each adapted to cooperate with a complementary retaining means 11 caliper type.
• the complementary retaining means 11 are attached to the fixed structure while the electric locks 10 are attached to the removable structure.
• the locking means may each be equipped with at least one stiffener supporting the lock.
• the stiffeners are associated with the slides 7, but this is not strictly necessary.
• Figures 1 and 2 show the removable structure respectively in closed and open position.
• the locking and unlocking controls of the electrical locking means are grouped at the level of an external control means of the nacelle and / or at the level of the cockpit of the aircraft.
• the retaining means 11, stirrup type, are positioned on the fixed structure of the nacelle in a zone ensuring the best structural rigidity to avoid any deflection of this interface.
• Each lock advantageously has a screw 12 for driving the hook protruding from the lock 10 towards the outside of the nacelle.
• a corresponding flap 13 may be provided in the outer panel 20 allowing access to one end of the screw 12.
• the tool may advantageously be guided by a fitting 14 fixed to the inside of the outer panel 20 at the level of the hatch 13.
• the manual drive can also be performed by means of a dedicated component of the type MDU 30 (Manual Drive Unit) linked to the driving motor of the electric lock 10.
• MDU 30 Manual Drive Unit
• a particular plug 15 having an appendage 15a adapted to cooperate with the screw 12 so as to block it.
• Such a cap will then mechanically inhibit the electric lock.
• This configuration is shown in Figure 6.
• the cap 15 may have an aerodynamic appendage visible from the outside of the nacelle to remind its presence.
• At least a portion of the locking means 10 are each associated with means for signaling their state of locking or unlocking and whose information can be raised to the cockpit or a control unit, for example.
• This signaling means may be in the form of a proximity detector disposed on the stirrup 11 facing one end of the hook 10 so as to obtain an "all or nothing" type signal and to ensure that the hook is honest and actually in place to fulfill its function.
• the signaling means is preferably placed on a fixed element (caliper, for example) in order to reduce the disconnection interfaces, which would reduce the reliability of the system.
• the locking means equipping a nacelle according to the invention also have pre-tensioning adjustment means.
• the pre-tensioning adjustment in mechanical locking systems is generally performed by positioning a load cell at the end of the handle, hook in contact on the caliper, then pulling on the load cell and verifying the traction value obtained. . When this value is not adequate, access to the caliper fixing system and adjust it to the axial position and then carry out the check again until the desired value is obtained.
• the pre-tension value can be controlled in various ways, such as by the voltage given to the motor during locking, by means of a manual drive system. using a torque wrench, a voltage sensor installed on one of the mechanical parts in contact and voltage such as the hook or the caliper, or by a torque limiter installed on one of the mechanical parts in contact and tension like the hook or the stirrup. These various means are used to control and monitor the voltage.
• the present locking means are also equipped with adjustment means for adjusting the pre-tension value when the removable structure is in the closed position.
• Figure 7 shows a first pretension adjusting means.
• a fitting 40 is disposed on the removable outer structure vis-à-vis the element to be adjusted (yoke 11 here) when said removable structure is in the closed position.
• An opening 41 is made in the fitting so as to allow the passage of an adjusting tool such as a key.
• the stirrup 11 is mounted to move in translation in the locking direction and has a slot 42 capable of receiving a heel 43 having a first end of small thickness and a second end of greater thickness.
• the access fitting 40 may be replaced by a hatch, for example, or any other means allowing access to the adjusting screw.
• Figure 8 shows a second pretension adjusting means.
• an access hatch 50 is formed in the outer wall 20 of the removable structure vis-à-vis the element to be adjusted (bracket 11 here) when said removable structure is in the closed position.
• a fitting access as described above is obviously possible.
• the pre-tension adjusting means comprises a worm 51 cooperating with a threaded end 52 of the caliper, so as to allow axial displacement of the latter when the worm 51 is rotated.
• a locking device 53 of the worm is added so as to ensure the maintenance of the adjustment over time.
• a specific abutment for reducing friction can be inserted between the fixed support and the adjustment nut.
• a torque limiter can also be added at the end of the auger, thus ensuring control of the tension in the caliper without the need to use a torque wrench.
• this system can be motorized to ensure a permanent identical voltage by permanent voltage control.
• the lock may be associated with a proximity detection of the removable upstream structure close to its closed position, said proximity detection being able to authorize the implementation of the lock. This ensures a good distance for gripping the stirrup by the hook. Proximity detection may be used also to trigger an automatic lock according to this approach of the removable structure.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Aviation & Aerospace Engineering (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

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ID=39735405

Family Applications (1)

Country Status (8)

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• 2008
  • 2008-01-18 FR FR0800265A patent/FR2926537B1/fr not_active Expired - Fee Related
  • 2008-11-28 EP EP08872248A patent/EP2229323A2/de not_active Withdrawn
  • 2008-11-28 US US12/811,347 patent/US8876041B2/en not_active Expired - Fee Related
  • 2008-11-28 WO PCT/FR2008/001659 patent/WO2009098402A2/fr not_active Ceased
  • 2008-11-28 CN CN200880124290.3A patent/CN101909999B/zh not_active Expired - Fee Related
  • 2008-11-28 CA CA2705887A patent/CA2705887C/fr not_active Expired - Fee Related
  • 2008-11-28 BR BRPI0821699-1A patent/BRPI0821699A2/pt not_active IP Right Cessation
  • 2008-11-28 RU RU2010133741/11A patent/RU2010133741A/ru not_active Application Discontinuation

Non-Patent Citations (1)

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