WO2011151577A2 - Nacelle pour turboréacteur avec dispositif de reprise d'efforts circonférentiels - Google Patents
Nacelle pour turboréacteur avec dispositif de reprise d'efforts circonférentiels Download PDFInfo
- Publication number
- WO2011151577A2 WO2011151577A2 PCT/FR2011/051212 FR2011051212W WO2011151577A2 WO 2011151577 A2 WO2011151577 A2 WO 2011151577A2 FR 2011051212 W FR2011051212 W FR 2011051212W WO 2011151577 A2 WO2011151577 A2 WO 2011151577A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- covers
- locking
- rod
- hook
- unlocking
- Prior art date
Links
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 29
- 238000011084 recovery Methods 0.000 claims description 57
- 210000003462 vein Anatomy 0.000 claims description 13
- 230000000903 blocking effect Effects 0.000 claims description 9
- 238000005304 joining Methods 0.000 claims description 3
- ORQBXQOJMQIAOY-UHFFFAOYSA-N nobelium Chemical compound [No] ORQBXQOJMQIAOY-UHFFFAOYSA-N 0.000 description 10
- 238000006073 displacement reaction Methods 0.000 description 9
- 230000001052 transient effect Effects 0.000 description 6
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000470 constituent Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 230000000717 retained effect Effects 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
- F02K1/64—Reversing fan flow
- F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
-
- 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
-
- 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
- F02K1/766—Control or regulation of thrust reversers with blocking systems or locking devices; Arrangement of locking devices for thrust reversers
Definitions
- the present invention relates to a nacelle for turbojet engine of an aircraft.
- turbojet engine nacelle comprising:
- a thrust reverser arranged downstream of the fan casing and comprising a cap defining with the internal structure an annular duct for the passage of an air flow, said cap delimiting an external line of said annular vein and comprising two dem i-removable covers respectively having upper edges equipped with hinge means of half-covers on the pylon, said hinge means being shaped to allow the pivoting of the half-covers between closed and open positions about longitudinal axes respective ones forming hinge lines.
- a nacelle 1 can be attached to a fixed structure SF of an aircraft or airplane, such as a wing, by means of a pylon or mast 2.
- the nacelle 1 has a structure comprising an air inlet section 3 upstream, a central section 4 surrounding a blower (not visible) of the turbojet, and a downstream section 5 surrounding the turbojet and housing a thrust reverser 50.
- the middle section 4 comprises a casing 41, said fan casing, attached at its upstream end to the air intake structure 3 and at its downstream end to the downstream section 5 and thus to the thrust reverser 50; this fan casing 41 being surrounded by an outer fan cowl 40.
- the fan casing 41 is fixed directly on the upstream portion 21 of the pylon 2, while the downstream portion 22 of the pylon 2 is fixed on the wing SF.
- the downstream section 5 further comprises an internal structure (not visible) surrounding the turbojet engine and partly defining an annular vein for the passage of a air flow, this internal structure delimiting an internal line of this annular vein.
- the tower 2 has in its upstream portion 21 a relatively thin or slightly thick structure compared to its downstream portion 22.
- the thrust reverser 50 comprises a cover defining with the internal structure the annular vein, this cover delimiting a external line LE (visible in Figure 3) of this annular vein.
- the thrust reverser 50 in the closed position is held on the downstream end of the fan casing 41 by a knife system inserted into a groove (not shown).
- the cover of the thrust reverser 50 comprises two removable half-covers 51 respectively having upper edges 52 equipped with hinge means 53 of the half-covers 51 on the pylon 2.
- These hinge means 53 are shaped to allow the pivoting of the half-covers 51 between closed and open positions about respective longitudinal axes forming LC lnigne lines.
- the articulation of half-covers 51 on the pylon 2 is achieved by means of floating rods 53 which define the hinge lines LC.
- the hoods 51 also have free bottom edges 54, opposite to the upper edges 52, which are generally provided with lower locking means (not shown, such as a latch or hook system) designed to keep closed. the half-covers 51 in the lower part of the nacelle 1 (at 6H).
- lower locking means may for example be actuated by a lower locking handle disposed on one of the lower edges 54 and movable between a lock position and an unlatching position of the lower locking means.
- the floating links 53 are installed through the pylon 2, downstream of the upstream portion 21 ( as shown in Figure 3) where the pylon 2 is thick enough to withstand a structural break induced by the openings through the connecting rods 53.
- the floating rods 53 are conventionally mounted with clearance through the pylon 2, so as not to enter. interference during relative movements of the different structures of the nacelle 1.
- this upper safety system is also attached to the two external fan cowl half-covers via a connecting rod slidably mounted in the groove of a guide mounted on the external half fan cowls.
- this higher security system allows to open the half-covers of the thrust reverser only when the external half blower covers are open.
- the invention has the aim of responding in all or part to the aforementioned problems by proposing a nacelle equipped with a sufficiently strong mechanical link between the two half-covers of the thrust reverser in order to be able to resume the efforts which tend to separate these half-covers from one another and break the attachment of the half-covers on the fan casing.
- Another object of the invention is to equip a nacelle with such a mechanical link between the half-covers that is disposed sufficiently close to the upstream end of the half-covers, closer to the attachment of the half-covers on the fan casing, so as not to risk detaching the attachment of the thrust reverser on the fan casing under very large displacements, especially during a rupture of fan blade.
- Another object of the invention is to equip a nacelle with a mechanical link between the half-covers sufficiently close to the upstream end of the half-covers, which does not require drilling or crossing the pylon at its part. upstream. Indeed, in this relatively upstream upstream portion of the pylon, the structure of the tower may not mechanically support a break in structural continuity induced by an opening.
- Another object of the invention is to equip a nacelle with a mechanical link between the half-covers which makes it possible to lock the half-covers in closing and to allow the half-covers to be opened, regardless of the opening situation. / closing the outer blower cover.
- a nacelle for turbojet engine of an aircraft comprising:
- a fan casing intended to surround a fan upstream of the turbojet engine, said fan casing being surrounded by an external fan cowl and being fixed on a support pylon of the nacelle;
- a thrust reverser disposed downstream of the fan casing and comprising a cap defining with the internal structure an annular vein for the passage of an air flow, said cap delimiting an external line of said annular vein and comprising two half removable covers respectively having upper edges equipped with hinge means of the half-covers on the pylon, said hinge means being shaped to allow the pivoting of the half-covers between closed and open positions around respective longitudinal axes forming hinge lines; and
- a device for taking up circumferential forces interconnecting the upper edges of the half-covers said force-taking device being shaped so as, on the one hand, to lock the half-covers in the closed position when it occupies a locking configuration and, on the other hand, to allow the opening of the half-covers when it occupies an unlocking configuration
- the nacelle according to the invention being remarkable in that the force recovery device is disposed under an upstream portion of the tower, upstream of the hinge means of the half-covers on the tower, and is interposed between the outer line of the annular vein and the two hinge lines, and in that the force-take-up device is attached only to the half-covers to enable or disable their half-covers independently of the opening / closing of the external blower hood.
- the force-taking device is disposed under the upstream portion of the pylon, offset from the hinge lines and above the outer line of the annular vein, so that it is located sufficiently close to the Upstream end of the half-covers, closer to the attachment of the half-covers on the fan casing, while forming a sufficiently strong mechanical link (in its configuration / locking position) to resume efforts that tend to separate these half-covers one of the other.
- This force recovery device connects transversely the upper edges of the half-covers, so that it is mounted in the upper part (or upper) of the nacelle at 12 o'clock.
- the force recovery device is not attached to the external fan cowl and its operation is independent of the opening / closing situation of the external fan cowl.
- the fan casing has, at its downstream end, upper fixing means of said fan casing on the upstream part of the pylon, and the force-taking device is disposed between said upper fixing means and the means hinge.
- the force recovery device comprises at least one jack equipped with a rod slidably mounted in a hollow body between a retracted position in the body and a deployed position out of the body, said rod presenting a first end attached to the upper edge of one of the half-covers and an opposite second end extending into the body, said body having a first end provided with a passage opening of the rod and an opposite second end secured to the upper edge of the other half-cover, and the cylinder further comprises locking / unlocking means cooperating with the rod to lock / unlock the rod in the retracted position.
- the jack may correspond to a system of constant link cylinder, it being understood that such a system of constant link cylinder designates a jack fixed permanently on the two half-covers of the thrust reverser, so that it is not necessary to disassemble one of the fasteners of the cylinder to allow the opening of the half-covers of the thrust reverser, the opening maneuver of the half-covers being allowed by the system internal cylinder during relaxation or output of the cylinder rod.
- the installation of the jack on the half-covers can be done at the same time as the mounting of the hinge means of the half-covers on the pylon, in the upper part of the nacelle (at 1 2 H).
- the unlocking command of the locking / unlocking means of the jack is preferably done remotely since the cylinder is, once installed, difficult to access as well as the hinge lines defined by the hinge means.
- the locking / unlocking means comprise:
- Locking means disposed in the body and cooperating with the rod, and in particular the second end of the rod, to lock it in its retracted position, said locking means being movably mounted in the body between a locking position and a position of unblocking of the rod;
- driving means designed to drive the locking means in displacement between the locking and unlocking positions and vice versa.
- the locking means comprise at least one hook piece having a free end designed to cooperate with the second end of the rod, said hook piece being movable in translation in the body between the locking position in which the free end of the hook piece cooperates with the second end of the rod and the unlocking position in which the free end of the hook piece is spaced from the second end of the rod and allows the movement of the rod.
- the locking means comprise a nut mounted on the thread of the rod inside the body and the drive means comprise a rotary motor designed to rotate the rod;
- the rotary engine is controlled by a system for opening the two half-covers of the thrust reverser so that the speed of rotation of the rod imposed by the rotary motor allows the nut to be driven in translation more rapidly; the opening of two demi-hoods by the opening system, so the rotary engine of the cylinder allows a clearance of clearance of the inner nut so that the latter does not interfere during the opening sequence of the half -capots; or alternatively
- the rotary motor is independent of a system for opening the two half-covers of the thrust reverser, and the rod has on its second end a piece forming a stop for the nut, and in this case the rotary motor of the cylinder performs the complete maneuver of disengagement of the nut before starting the opening sequence of the half-covers.
- the present invention also relates to the following characteristics:
- the cylinder locks the half-covers in an optional direction, either in compression (direction of retraction of the rod) or in extension (direction of exit or expansion of the rod) relative to the axis of the cylinder, according to the need those skilled in the art, or alternatively the cylinder locks the half-covers in both directions simultaneously (both in compression and extension);
- the jack is locking and / or electric drive, or alternatively the cylinder is locking and / or mechanical drive;
- the jack is coupled to an opening system of the half-covers, and more particularly coupled to the opening logic of the half-covers;
- the jack has latching means at the end of closing, these locking means at the end of closure being preferably shaped to assist in the closing maneuver of the half-covers;
- the cylinder is associated with a maneuvering system opening the half-covers simultaneously, and in this case the cylinder motor (for driving the rod) is maneuvered at the same time as the opening command of the half -capots of the thrust reverser; or alternatively
- the jack is associated with a system for opening the half-cowls in sequential mode, and in this case the jack motor (for driving the rod) is operated before the opening command of the half-cowls. of the thrust reverser.
- the force recovery device comprises at least one locking system provided with:
- a hooking element mounted on the upper edge of the other half-cover, said hook being movable between a locking position in which the hook cooperates with the retaining element in the closed or substantially closed position of the half-covers, and an unlocking position in which the hook does not cooperate with the attachment element and allows the opening of the half-covers;
- the latch system corresponds to a disconnectable link system, for remotely disconnecting or disconnecting the connection between the two half-covers when the latch system is in the unlocked position.
- the nacelle further comprises lower locking means arranged on the lower free edges of the half-covers opposite to the upper edges and designed to keep closed the half-covers, said lower locking means being actuated by a lower handle of locking arranged on one of said lower edges and movable between a locking position and an unlocking position of the lower locking means
- the actuating means of the latch system comprises an actuating handle connected to the hook and disposed on the one of the lower edges of the half-covers, said actuating handle being movable between a locking position and a release position of the hook
- the lower locking handle and the operating handle are arranged relative to each other relative to the other so that the lower locking handle prohibits the m actuating the actuating handle and locks it in its locking position as long as said lower locking handle is in its locking position.
- the upper edges of the half-covers support abutments which abut one against the other in a junction plane of the half-covers when they are in the closed position, and the attachment element the latch system is fixedly mounted on the upper edge of the half-cover concerned and extends substantially in said junction plane.
- the upper edges of the half-covers support abutments that bear against one another in a junction plane of the half-covers when they are in the closed position, and the fastening element of the system.
- latch is mounted on the upper edge of the half-cover concerned by means of a locking rod having a first portion hinged to said upper edge and a second portion movable relative to the first portion and supporting said member; hooking, so that said hooking element extends in a plane laterally offset with respect to the junction plane.
- This second part of the locking rod advantageously has guide means mounted on the pylon.
- the present invention also relates to the following features:
- the latch system is a centered hook system, that is to say that the hook is substantially in the junction plane between the two half-covers;
- the latch system is an eccentric hook system, that is to say that the hook is shifted transversely with respect to the junction plane between the two half-covers, being closer to one of the half-covers than the other.
- the force-taking device when using a locking system with a jack, is positioned as close as possible to the inner face of the pylon, and more particularly to the inner face of the upstream part of the pylon, with a wide distribution of the gripping points of the force-taking device on the half-covers and the points of articulation of the half-covers on the pylon.
- the kinematics of the locking / unlocking maneuver of the force take-up device ensures that there is little or no approximation to the inner face of the pylon regardless of the opening amplitude of the half-covers.
- FIG. 3 is a partial schematic side view of the nacelle of FIG. 2, illustrating the downstream end of the fan casing and the upstream part of the pylon;
- FIG. 4 is a schematic cross-sectional view of a nacelle according to the invention, in a sectional plane of the thrust reverser;
- FIG. 5 is an enlarged view of the zone v of FIG. 4;
- FIGS. 6a to 6g are schematic sectional views of a first force recovery device for a nacelle according to the invention, in different positions or configurations;
- FIGS. 7a and 7b are schematic sectional views of a second force recovery device for a nacelle according to the invention, in two different positions or configurations;
- FIGS. 8a to 8f are schematic sectional views of a third force recovery device for a nacelle according to the invention, in different positions or configurations;
- FIGS. 9a to 9d are schematic sectional views of a fourth force recovery device for a nacelle according to the invention, in different positions or configurations;
- FIGS. 10a to 10d are schematic sectional views of a fifth force recovery device for a nacelle according to the invention, in different positions or configurations.
- a nacelle 1 according to the invention is of the same type as that described above with reference to FIGS. 1 to 3, with the difference that it furthermore comprises a device for taking up circumferential forces, as one of the devices. 6, 7, 8, 9, 1 0 illustrated respectively in FIGS. 6 to 9.
- the force-taking device 6, 7, 8, 9, 10 interconnects the upper edges 52 of the half-covers 51 of the thrust reverser 50, and is therefore situated in the upper part of the nacelle 1, otherwise 12H, as shown in Figures 4 and 5.
- the force-taking device 6, 7, 8, 9, 10 is located in a zone Z (illustrated in FIG. 3) below the upstream portion 21 of the pylon 2. above or close to the outer line line LE of the annular vein and offset from the hinge lines LC, so that this force-taking device 6, 7, 8, 9, 10 is interposed between the line external LE of the annular vein and the two LC hinge lines and is sufficiently close to the upstream end of the half-covers 51, closer to the attachment of the half-shells 51 on the fan casing 41 to be able to resume the efforts which tend to separate these half-covers 51 from one another.
- the force-taking device 6, 7, 8, 9, 10 is designed to occupy:
- the force-taking device 6, 7, 8, 9, 10 is positioned as close as possible to the inner face of the pylon 2, and more particularly to the internal face of the upstream portion 21. of the pylon 2, with a substantially balanced distribution of the attachment points PA1, PA2 of the force-taking device 6, 7, 8, 9, 10 on the half-covers 51 (and more specifically on the upper edges 52 of the half 51) and pivot points 53 of the half-covers 51 on the pylon 2.
- the attachment points are referenced PA1 when the ispositive of recovery of forces is in configuration / position of locking and the half covers 51 are in the closed position, and are referenced PA2 when the force recovery device is in the configuration / unlocking position and the half-covers 51 are in the open position.
- the force taking-up device 6 is made in the form of a cylinder system with constant links and interconnection.
- This force recovery device 6 comprises a jack equipped with a rod 61 slidably mounted in a hollow body 62 between a retracted position in the body 62 and a deployed position outside the body 62.
- the rod 61 has a first end 61 1 articulated on the upper edge of one of the half-covers and an opposite second end 612 extending into the body 62; this first end 61 1 forming an anchor point of the force recovery device 6 on one of the half-covers.
- the second end 612 of the rod 6 has an outgrowth.
- Two stops, respectively internal 613 and external 614, are fixed on the rod 61 to limit the movement, either in the direction of the output (movement to the deployed position) or in the direction of re-entry (movement to the position retracted).
- the body 62 has a first end 621 provided with a passage opening of the rod 61 and a second end 622 opposite full articulated on the upper edge of the other half-cover; this second end 622 forming an anchor point of the force recovery device 6 on the other half-cover.
- the body 62 has on its inner face a degree or hollow 620, for example in the form of a reduction in thickness from the second end 622 to the first end 621 of the body 62; this degree or hollow 620 having a ramp shape and being located at a predetermined distance from the second end 622 of the body 62.
- the force take-up device 6 further comprises means for locking / unlatching the cooperating element with the key 61 to lock / unlock the rod 61 in the retracted position.
- These locking / unlocking means comprise:
- a hook member 63 disposed in the bottom of the body 62, opposite its first end 621, and adapted to cooperate with the exfroissance of the second end 612 of the rod 61 to block it in its position retracted, this hook member 63 being movable in the body 62 between a locking position and a release position of the rod 61;
- drive means 64, 65 designed to drive the hook piece 63 in displacement between the locking and unlocking positions and vice versa.
- the hook part 63 comprises at least two fingers having first hook-shaped free ends adapted to grip and block the protrusion of the second end 612 of the rod 61.
- the drive means comprise a slider 64 on which are pivotally mounted the fingers of the hook piece 63, and a translational movement system (not shown) of the slider 64, as shown in FIG. a motor (preferably electric) or a remote-operated manual system, such as a rotation-driven or traction-driven cable device.
- the fingers of the hook piece 63 have second ends opposite to the first ends, articulated on the slide 64.
- the slider 64 may for example have an external thread and be mounted inside a nut 65 disposed in the bottom of the body 62; this nut 65 being rotated, for example by a rotary motor, thus leading to the translational movement of the slide 64.
- the principle of this first embodiment consists in unlocking the locking means, in this case the hook piece 63, from the rod 61, in order to let the rod 61 freely move during the opening maneuver of one at least two half-covers of the thrust reverser.
- the locking / unlocking means of the force-taking device are activated at the end of closing of the half-covers to complete this closing operation and finally lock the demi -caps in the closed position by locking the rod 61 in its retracted position.
- this force recovery device 6 is described below with reference to FIGS. 6a to 6g, which illustrate successive configurations of the force recovery device 6.
- FIG. 6a illustrates the force-taking device 6 in the locking configuration, when the half-covers are in the closed position, where the rod 61 is in the retracted position with the fingers of the hook-forming piece 63 which hook the protuberance of the second end 612 of the rod 61, thereby blocking the rod 61 in the direction of the exit (to the left in the figure); the outer stop 614 being in abutment against the first end 621 of the body 62, thus blocking the rod 61 in the direction of re-entry (to the right in the figure).
- FIG. 6b illustrates the beginning of the unlocking maneuver of the force recovery device 6, at the same time at the beginning of the opening maneuver of one or both half-covers, where the slide 64 starts to move in the direction of the first end 621 of the body 62, as shown schematically by the arrow CS, leading to the displacement of the fingers of the hook piece 63 towards the degree or hollow 620 provided on the inner face body 62; the fingers of the hook piece 63 becoming detached from the protuberance of the second end 612 of the rod 61.
- FIG. 6c illustrates the unlocking of the force recovery device 6, where the slide 64 has moved until the fingers of the hook piece 63 reach and engage in the degree or hollow 620 provided on the internal face of the body 62 and are spaced from each other, according to an opening movement of the petal type, by means of an elastic element (not shown) shaped to spread and move the fingers of the piece forming hook 63 from each other; the spacing of the fingers of the hook piece 63 is such that from now on these fingers can no longer cooperate with the protuberance of the second end 612 of the rod 61 and thus can no longer lock the rod 61, so that the rod 61 is free to debate in the direction of the exit.
- FIG. 6d illustrates the force recovery device 6 which is unlocked when opening the half-covers of the thrust reverser, where said force-taking device 6 allows this opening of the half-covers.
- the head 61 is now free from any rectilinear movement, as shown by the arrow TL, and the jack acts as a simple piston without maneuvering force when opening the half-covers.
- FIG. 6e illustrates the force recovery device 6 which is unlocked during the closing of the half-covers of the thrust reverser.
- the rod 61 enters the body 62, as shown by the arrow TR, until reaching a transient position close to the locking position shown in Figures 6a and 6b, where the external stop 614 is not yet in abutment against the first end 621 of the body 62.
- some parameters that the rod 61 can not reposition themselves in end-of-stroke limit such as the flexibility of the structure, the joints of sealing, the manufacturing and positioning tolerances of the elements constituting the force-taking device 6.
- the protuberance of the second end 61 2 of the rod 61 is positioned inside the fingers of the part forming a hook 63.
- FIG. 6f illustrates the beginning of the locking maneuver of the force recovery device 6, where the rod 61 is in its transient position and the slider 64 begins to move towards the second end 622 of the body 62, as schematized by the arrow CR, leading to the displacement of the fingers of the hook forming piece 63 in this same direction, resulting in the disengagement of the fingers of the hook piece 63 out of the degree or hollow 620 (the ramp form facilitating this disengagement).
- the fingers of the hook piece 63 come closer to each other and close on the protuberance of the second end 61 2 of the rod 61 to come block this rod 61; the transient position of the rod 61 is such that a clearance between the first hook-free free ends of the fingers and the protrusion of the rod 61 is provided to allow the fingers to retract on the rod 61 without constraint.
- the assurance of the correct positioning of the protrusion of the rod 61 relative to the fingers can be done by any suitable detection means and known to those skilled in the art, such as for example a proximity detector.
- FIG. 6g illustrates the end of the locking maneuver of the force-taking device 6, where the slide 64 ends moving towards the second end 622 of the body 62, as shown by the arrow CR, so that the The fingers of the hook piece 63 bear against the protuberance of the second end 612 of the rod 61 and that these fingers drive the rod 61 to the locking position illustrated in Figures 6a and 6b.
- the force recovery device 6 continues the rectilinear reclosure movement of the rod 61 until it comes to an end stop. At the end of this movement, the drive means are automatically disconnected and locked in position.
- the force taking-up device 7 is designed as a constant-link cylinder and screw / nut system.
- This force recovery device 7 comprises a jack equipped with a rod 71 at least partially threaded and slidably mounted in a hollow body 72 between a retracted position in the body 72 and a deployed position out of the body 72.
- the rod 71 has a first end 71 1 hinged to the upper edge of one of the half-covers and an opposite second end 712 extending into the body 72; this first end 71 1 forming an anchor point of the force taking up device 7 on one of the half-covers.
- Two stops, respectively internal 713 and external 714, are fixed on the rod 71 to limit the movement, whether at the output or at the input; the internal stop 713 being fixed on the second end 712 of the rod 71.
- the force recovery device 7 further comprises locking / unlocking means cooperating with the rod 71 to lock / unlock the rod 71 in the retracted position. These locking / unlocking means comprise:
- a rotary motor 74 designed to rotate the rod 71, where the rotary motor 74 is controlled, via links 75, by an opening system (not shown) of the two half-covers of the thrust reverser so that that the speed of rotation of the rod 61 imposed by the rotary motor 74 allows the nut 73 to be driven in translation more rapidly than the opening of two half-covers by the opening system
- the principle of this second embodiment consists in unlocking the locking means, in this case the nut 73, of the rod 71, in order to let the rod 71 freely debate during the opening maneuver of one of the less than two half-covers of the thrust reverser.
- the locking / unlocking means of the force taking-up device 7 are actuated at the end of closing of the half-covers to complete this closing operation and lock in the end the demi -caps in closed position by locking the rod 71 in its retracted position.
- the locking / unlocking of the force recovery device 7 is performed in synchronization with the opening / closing of the half-covers made by the opening system.
- the rod 71 slides freely through the body 72 with the association of the nut 73 stopped in translation between the first end 721 of the body 72 and the internal abutment 713 provided on the rod 71.
- the stem is threadedly threaded through the body, more specifically on the first end of the body.
- FIGS. 7a and 7b illustrate two successive configurations of the force-taking device 7.
- FIG. 7a illustrates the force recovery device 7 in the locking configuration, when the half-covers are in the closed position, where the rod 71 is in the retracted position, with the nut 73 abutting against the first end 721 of the body 72 thus blocking the rod 71 in the direction of the exit (to the left in the figure), and with the external stop 714 being in support against the first end 721 of the body 72 thus blocking the rod 71 in the direction of re-entry (to the right in the figure).
- FIG. 7b illustrates the unlocking maneuver of the force recovery device 7, simultaneously with the opening maneuver of one or both half-cowls, where the opening system of the half-cowls controls the rotary motor 74 for rotating the rod 71 (as shown by the arrow R) in rotation with a speed greater than that of the opening of the half-covers, causing the nut 73 to move towards the second end 712 of the rod 71, as schematized by the arrow DE. The nut 73 then comes off the first end 721 of the body 72, thereby allowing the outlet of the rod 71.
- the differential speed causes the nut 73 to move away from the first end 721 of the body 72 more rapidly than the rod 71 moves towards the outlet, ie towards the extended position; the purpose being to prevent the nut 73 does not interfere with this rod outlet 71 and thus the opening of the half-covers.
- the length of the rod 71 is defined so that the nut 73 does not come into contact with the internal stopper 713 provided on the second end 712 of the rod 71 before the end of the complete opening of the half-covers of the inverter thrust.
- the cylinder can maneuver without stress when opening the half-covers.
- the locking maneuver of the force recovery device 7 is carried out concomitantly with the closing maneuver of the half-covers, on the same principle as described below with the rod 71 which enters the body 72, the rotary motor 74 rotates in the other direction and the nut 73 comes into contact with the first end 721 of the body 72.
- the force taking-up device 8 is also embodied in the form of a system of constant-link cylinder and screw / nut.
- This force recovery device 8 comprises a jack equipped with a rod 81 at least partially threaded and slidably mounted in a hollow body 82 between a retracted position in the body 82 and a deployed position out of the body 82.
- the rod 81 has a first end 81 1 articulated on the upper edge of one of the half-covers and an opposite second end 812 extending into the body 82; this first end 81 1 forming an anchor point of the force recovery device 8 on one of the half-covers.
- Two stops, respectively internal 813 and external 814, are fixed on the rod 81 to limit the movement, either at the output or at the input; the internal stop 813 being mounted on the second end 812 of the rod 81.
- the force recovery device 8 further comprises locking / unlocking means cooperating with the rod 81 to lock / unlock the rod 81 in the retracted position.
- These locking / unlocking means comprise:
- a rotary motor 84 designed to rotate the rod 81.
- this rotary motor 84 of the third embodiment is independent of a system for opening the two half-covers of the thrust reverser.
- the rotary motor 84 may be of the electric or manual drive type.
- the principle of this third embodiment consists in unlocking the locking means, in this case the nut 83, of the rod 81, in order to release the stem 81 freely to debate and to authorize the opening maneuver of one at least two half-covers of the thrust reverser.
- the locking / unlocking means of the force recovery device 8 are actuated at the end of closing of the half-covers to complete this closing maneuver and lock in the final dem i-caps in the closed position by locking the rod 81 in its retracted position, by bringing the nut 83 in abutment against the first end 821 of the body 82.
- the locking / unlocking of the force taking-up device 8 is performed sequentially with respect to the opening / closing of the half-covers made by the opening system of the half-covers.
- the rod 81 slides freely through the body 82 with the combination of the nut 83 stopped in translation between the first end 821 of the body 82 and the internal abutment 813 provided on the rod 81.
- FIGS. 8a to 8f illustrate successive configurations of the force recovery device 8.
- FIG. 8a illustrates the force recovery device 8 in the locking configuration, when the half-covers are in the closed position, where the rod 81 is in the retracted position, with the nut 83 abutting against the first end 821 of the body 82 thus blocking the rod 81 in the direction of the exit (to the left in the figure), and with the outer stop 814 bearing against the first end 821 of the body 82 thus blocking the rod 81 in the sense of reentry (to the right in the figure).
- the rotary motor 84 is actuated and rotates the rod 81 (as shown schematically by the arrow R), causing the displacement of the nut 83 towards the second end 812 of the rod 81, as shown schematically by the arrow DE.
- FIG. 8b illustrates the end of the unlocking maneuver of the force-taking device 8, in which the nut 83 has been moved unlocking maneuver until it bears against the internal stop 813 provided on the second end 812 of the stem 81. If the motor 84 is electrically driven, it is no longer powered at the end of this unlocking maneuver.
- FIG. 8c illustrates the force recovery device 8 in the unlocked configuration allowing the opening of the half-covers of the thrust reverser.
- the cylinder then acts as a simple piston without maneuvering force when opening the half-covers, the nut 83 remaining in abutment against the internal stop 813.
- Figure 8d it l ustre l e ispositif resumption of efforts 8 in unlocked configuration allowing the closing of the half-covers of the thrust reverser.
- the closing maneuver of the half-covers is engaged, the rod 81 is free to debate freely and to enter the body
- the jack always acts as a simple piston without any maneuvering constraint when closing the half-covers, the nut 83 still resting against the internal stop 81 3.
- the rod 81 enters the body 82 until it reaches a position transient close to the locking position illustrated in Figures 8a and 8b, where the outer stop 814 is not yet in abutment against the first end 821 of the body 82. Indeed, some parameters that the rod 81 can not alone repositioning in end-stop, such as the flexibility of the structure, the seals, the manufacturing and positioning tolerances of the constituent elements of the force recovery device 8.
- FIG. 8e illustrates the beginning of the locking maneuver of the force recovery device 8, where the rod 61 is in its transient position and where the rotary motor 84 rotates the rod 81, in the opposite direction with respect to previously , so that the nut 83 begins to move towards the first end 821 of the body 82, as shown by the arrow RE, leading the nut 83 to bear against this first end 821 of the body 82.
- the force recovery device 9 is made in the form of a centrally disconnectable linkage system.
- This force recovery device 9 comprises a latch system positioned approximately in a median plane of the nacelle, corresponding substantially to the junction plane of the two half-covers 51 of the thrust reverser.
- This lock system comprises:
- the upper edges 52 of the half-covers 51 support abutments 55 which bear against each other in the joining plane of the half-housings. covers 51 when in the closed position.
- the latching element 92 of the latch system is fixedly mounted on the upper edge 52 of the half-cover 51 concerned and extends substantially in this junction plane.
- the actuating means may be shaped to actuate the remote lock system electrically or manually (mechanically).
- the actuation is manual and is performed by a cable return 94 on an actuating handle 93 disposed in the lower part of the nacelle (6H).
- the actuating means of the locking system comprise the actuating handle 93 connected to the hook 91 by a cable control 94, this actuating handle 93 being disposed on one of the lower (not visible) edges of the half-covers 51.
- the actuating handle 93 is movable between a locking position and an unlocking position of the hook 91.
- the nacelle further comprises lower locking means (not visible and in particular of the lock type) arranged on the lower free edges of the half-covers 51 and designed to keep closed the half covers 51, so that these lower locking means are arranged in the lower part of the nacelle (at 6H).
- These lower locking means are actuated by a lower PIV locking handle positioned on one of these lower edges, that is to say in the lower part of the nacelle (at 6H), and this lower PIV locking handle is movable between a position locking and an unlocking position of the lower locking means.
- the lower PIV locking handle and the actuating handle 93 are relatively relatively to one another so that the lower PIV locking handle prevents operation of the actuating handle 93. and locks it in its locking position as long as this lower PIV lock handle is in its locking position.
- the reclosing of the half-covers 51 of the thrust reverser can only be done when the locking is done (crocjet 91 in the locked position) with the actuating handle 93 closed in the locked position.
- FIGS. 9a to 9d illustrate successive configurations of the force recovery device 9 and the half-covers 51.
- FIG. 9a illustrates the force recovery device 9 in the locking configuration with the half-covers 51 in the closed position, where the hook 91 cooperates with the retention element 92, the actuating handle 93 is in position. locking position, and the lower locking handle PIV is in the locking position so that it prohibits the actuating handle maneuver 93.
- the hook 91 is advantageously provided to lock at three points exceeded to ensure lock security .
- FIG. 9b illustrates the beginning of the opening maneuver of the half-covers 51, with the force-taking device 9 still in the locking configuration and the half-covers 51 still in the closed position, where the hook 91 still cooperates with retained with the hooking element 92, the actuating handle 93 is still in the locking position, and the lower locking handle PIV is now in the unlocking position.
- the half-covers 51 can not yet open because the recovery device force release position 9 is in the locking configuration.
- FIG. 9c illustrates the continuation of the opening maneuver of the half-covers 51, where the actuating handle 93 has tilted into its unlocked position, following the prior tilting of the lower locking handle PIV in its unlocking position.
- the hook 91 disengages from the hooking member 92 and the force take-up device 9 goes into the unlocking configuration.
- FIG. 9d illustrates the end of the opening maneuver of the half-covers 51, where at least one of the half-covers 51 can open by pivoting around its articulation points 53, as shown by the arrow P because the force-taking device 9 is in the unlocking configuration, as is the lower locking means.
- the force recovery device 10 is designed as an off-center disconnectable connection system.
- This force recovery device 10 comprises a lock system offset from a median plane of the nacelle corresponding substantially to the junction plane of the two half-covers 51 of the thrust reverser.
- This lock system comprises: a hook 101 mounted on the upper edge 52 of one of the half-covers 51, partly lateral to the junction plane of the half-covers 51, advantageously in a reinforced zone of the half-cover 51 concerned;
- the upper edges 52 of the half-covers 51 support abutments 55 which bear against each other in the junction plane of the half-covers 51 when in the closed position.
- the latching element 102 of the latch system is mounted on the upper edge 52 of the half-cover 51 concerned via a locking rod 103 having a first portion 105 hinged to the upper edge 52 and a second Part 1 04 movable relative to the first part 105 and supporting the attachment element 102, so that the attachment element 102 extends in a plane laterally offset from the junction plane.
- the second portion 104 of the locking rod 103 has guide means 106 mounted on the pylon 2.
- the locking rod 103 is thus articulated around its attachment point on the half-cover 51 (at its first part 105), and it is guided in its kinematics by the guide means 106 which can be carried by the pylon 2.
- the attachment element 102 mounted on the locking rod 103, remains close to the structure of the pylon 2 by the guiding means 106 when opening the half-covers 51 to avoid any interference with the surrounding structures.
- the arrangement of the guide means 106 is provided to allow the hook 101 to catch or catch the fastening element 102 without restraint when the half-covers 51 are closed again.
- the actuating means may be shaped to actuate the remote lock system electrically or manually (mechanically).
- the actuation is manual and is performed by a cable return 108 on an actuating handle 107 disposed in the lower part of the nacelle (6H).
- the actuating means of the locking system comprise the actuating handle 107 connected to the hook 101 by a cable control 108, this actuating handle 108 being placed on one of the lower edges (not visible). half-covers 51.
- the actuating handle 107 is movable between a locking position and an unlocking position of the hook 101.
- the nacelle furthermore comprises lower locking means (not visible and in particular of the lock type) arranged on the lower free edges of the half-covers. 51 and designed to keep closed the half-covers 51, so that these lower locking means are arranged in the lower part of the nacelle (at 6H).
- These lower locking means are actuated by a lower PIV locking handle disposed on one of these lower edges, that is to say in the lower part of the nacelle (at 6H), and this lower PIV locking handle is movable between a position of locking and an unlocking position of the lower locking means.
- the lower PIV locking handle and the actuating handle 107 are relatively relatively to one another so that the lower PIV locking handle prevents operation of the actuating handle 107. and locks it in its locking position as long as this lower PIV lock handle is in its locking position.
- FIGS. 10a to 10d illustrate successive configurations of the force recovery device 10 and the half-covers 51.
- FIG. 10a illustrates the force recovery device 10 in the locking configuration with the half-covers 51 in the closed position, where the hook 101 co-operates with the attachment element 102, the actuating handle 107 is in the locked position, and the lower PIV locking handle is in the locking position so that it prohibits actuating handle maneuver 107.
- the locking rod 103 is in the closed position.
- FIG. 10b illustrates the beginning of the opening maneuver of the half-covers 51, with the reevaluation device 10 still in the locking configuration and the half-covers 51 still in the closed position, where the hook 101 always cooperates with the retaining element 102, the actuating handle 107 is still in the locking position, the locking rod 103 is still in the closed position, and the lower lock handle P IV is now in the unlock position.
- the half-covers 51 can not yet open because the release device force release position 10 is in the locking configuration.
- FIG. 10c illustrates the continuation of the opening maneuver of the half-covers 51, where the actuating handle 107 has tilted to its unlocking position, following the prior tilting of the lower PIV locking handle to its unlocked position. .
- the hook 101 disengages from the hooking member 102 and the force take-up device 10 goes into the unlocking configuration with the locking rod 103 still in the closed position.
- FIG. 10d illustrates the end of the opening maneuver of the half-covers 51, where at least one of the half-covers 51 can pivotally open around its articulation points 53, as shown by the arrow P because the force-taking device 10 is in the unlocking configuration, as are the lower locking means, the locking rod 103 passing in the open position with the relative displacement of the first and second parts 105, 104 of the connecting rod 103 concomitantly the pivoting of the first portion 105 of the connecting rod 103 with the guidance on the pylon 2.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Wind Motors (AREA)
- Body Structure For Vehicles (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2801400A CA2801400A1 (fr) | 2010-06-03 | 2011-05-27 | Nacelle pour turboreacteur avec dispositif de reprise d'efforts circonferentiels |
EP11726912.6A EP2576346A2 (fr) | 2010-06-03 | 2011-05-27 | Nacelle pour turboréacteur avec dispositif de reprise d'efforts circonférentiels |
CN2011800273179A CN102939244A (zh) | 2010-06-03 | 2011-05-27 | 包括用于吸收周向应力的设备的涡轮喷气发动机舱 |
BR112012030428A BR112012030428A2 (pt) | 2010-06-03 | 2011-05-27 | nacela de mecanismo motor de turbojato que inclui um dispositivo para absorção de tensões diferenciais |
RU2012156112/11A RU2012156112A (ru) | 2010-06-03 | 2011-05-27 | Гондола турбореактивного двигателя с устройством для восприятия окружных усилий |
US13/692,227 US8869506B2 (en) | 2010-06-03 | 2012-12-03 | Turbojet engine nacelle including a device for absorbing circumferential stresses |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1054323A FR2960855A1 (fr) | 2010-06-03 | 2010-06-03 | Nacelle pour turboreacteur avec dispositif de reprise d'efforts circonferentiels |
FR1054323 | 2010-06-03 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/692,227 Continuation US8869506B2 (en) | 2010-06-03 | 2012-12-03 | Turbojet engine nacelle including a device for absorbing circumferential stresses |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2011151577A2 true WO2011151577A2 (fr) | 2011-12-08 |
WO2011151577A3 WO2011151577A3 (fr) | 2012-09-13 |
Family
ID=43478320
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2011/051212 WO2011151577A2 (fr) | 2010-06-03 | 2011-05-27 | Nacelle pour turboréacteur avec dispositif de reprise d'efforts circonférentiels |
Country Status (8)
Country | Link |
---|---|
US (1) | US8869506B2 (fr) |
EP (1) | EP2576346A2 (fr) |
CN (1) | CN102939244A (fr) |
BR (1) | BR112012030428A2 (fr) |
CA (1) | CA2801400A1 (fr) |
FR (1) | FR2960855A1 (fr) |
RU (1) | RU2012156112A (fr) |
WO (1) | WO2011151577A2 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104603401A (zh) * | 2012-08-27 | 2015-05-06 | 埃尔塞乐公司 | 用于固定机舱前框架和涡轮喷气发动机外壳界面的组件 |
EP2951091A4 (fr) * | 2013-01-29 | 2016-08-03 | United Technologies Corp | Capot avec verrou à taux limité |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2953490B1 (fr) * | 2009-12-07 | 2012-02-24 | Aircelle Sa | Ensemble arriere de nacelle pour turboreacteur |
US8720183B2 (en) * | 2011-03-02 | 2014-05-13 | Spirit Aerosystems, Inc. | Thrust reverser translating sleeve assembly |
US10458280B2 (en) * | 2013-03-13 | 2019-10-29 | United Technologies Corporation | Gas turbine engine hydraulically operated nacelle latch |
FR3036382B1 (fr) * | 2015-05-21 | 2017-06-16 | Airbus Operations Sas | Nacelle d'aeronef comportant au moins un capot monte rotatif autour de l'axe longitudinal de la nacelle |
US10479517B2 (en) * | 2016-12-05 | 2019-11-19 | The Boeing Company | Composite fan cowl with a core having tailored thickness |
US10570854B2 (en) * | 2017-08-18 | 2020-02-25 | Woodward, Inc. | Three actuator cascade type thrust reverser actuation system |
US11441514B2 (en) | 2018-10-02 | 2022-09-13 | Woodward, Inc. | Tertiary lock |
US11155343B2 (en) * | 2018-12-17 | 2021-10-26 | The Boeing Company | Brake systems for aircraft and related methods |
GB201909171D0 (en) | 2019-06-26 | 2019-08-07 | Rolls Royce Plc | Gas turbine engine cowl doors |
US11788490B1 (en) * | 2022-12-05 | 2023-10-17 | Woodward, Inc. | Traveling finger lock for an actuator |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4679750A (en) | 1984-06-20 | 1987-07-14 | The Boeing Company | Latch system |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3541794A (en) * | 1969-04-23 | 1970-11-24 | Gen Electric | Bifurcated fan duct thrust reverser |
GB1318748A (en) * | 1970-08-11 | 1973-05-31 | Secr Defence | Gas turgine ducted fan engines for aircraft |
US4421349A (en) * | 1981-12-28 | 1983-12-20 | The Boeing Company | Cowling latch |
US4549708A (en) * | 1982-08-31 | 1985-10-29 | United Technologies Corporation | Cowling latch system |
FR2560854B1 (fr) * | 1984-03-07 | 1986-09-12 | Snecma | Capotages structuraux participant a la rigidite d'ensemble d'un turboreacteur |
US4585189A (en) * | 1984-10-22 | 1986-04-29 | Lockheed Corporation | Counterbalanced cowling assembly for a pylon-mounted engine and nacelle therefor |
US5350136A (en) * | 1993-05-14 | 1994-09-27 | United Technologies Corporation | Nacelle arrangement |
US6189832B1 (en) * | 1998-04-03 | 2001-02-20 | Hartwell Corporation | Permanently connected remote latch mechanism |
US6517027B1 (en) * | 2001-12-03 | 2003-02-11 | Pratt & Whitney Canada Corp. | Flexible/fixed support for engine cowl |
US20050024815A1 (en) * | 2003-07-29 | 2005-02-03 | Pratt John D. | Latch fuse |
US6843449B1 (en) * | 2004-02-09 | 2005-01-18 | General Electric Company | Fail-safe aircraft engine mounting system |
US7275362B2 (en) * | 2004-09-08 | 2007-10-02 | The Boeing Company | Thrust reversers including latching mechanisms and methods for manufacturing such thrust reversers |
FR2896481B1 (fr) * | 2006-01-23 | 2009-12-04 | Aircelle Sa | Systeme de fixation pour element constitutif d'une nacelle de turboreacteur |
FR2914700B1 (fr) * | 2007-04-04 | 2009-05-22 | Aircelle Sa | Inverseur de poussee pour moteur a reaction |
FR2920177B1 (fr) * | 2007-08-20 | 2009-09-18 | Aircelle Sa | Dispositif de liaison, destine a relier un premier et second elements mobiles l'un par rapport a l'autre |
FR2921900B1 (fr) * | 2007-10-05 | 2011-03-18 | Aircelle Sa | Ensemble propulsif pour aeronef. |
FR2926285B1 (fr) * | 2008-01-15 | 2009-12-11 | Aircelle Sa | Nacelle a capotage simplifie |
-
2010
- 2010-06-03 FR FR1054323A patent/FR2960855A1/fr not_active Withdrawn
-
2011
- 2011-05-27 CN CN2011800273179A patent/CN102939244A/zh active Pending
- 2011-05-27 WO PCT/FR2011/051212 patent/WO2011151577A2/fr active Application Filing
- 2011-05-27 RU RU2012156112/11A patent/RU2012156112A/ru not_active Application Discontinuation
- 2011-05-27 CA CA2801400A patent/CA2801400A1/fr not_active Abandoned
- 2011-05-27 BR BR112012030428A patent/BR112012030428A2/pt not_active IP Right Cessation
- 2011-05-27 EP EP11726912.6A patent/EP2576346A2/fr not_active Withdrawn
-
2012
- 2012-12-03 US US13/692,227 patent/US8869506B2/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4679750A (en) | 1984-06-20 | 1987-07-14 | The Boeing Company | Latch system |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104603401A (zh) * | 2012-08-27 | 2015-05-06 | 埃尔塞乐公司 | 用于固定机舱前框架和涡轮喷气发动机外壳界面的组件 |
CN104603401B (zh) * | 2012-08-27 | 2016-04-13 | 埃尔塞乐公司 | 用于固定机舱前框架和涡轮喷气发动机外壳界面的组件 |
EP2951091A4 (fr) * | 2013-01-29 | 2016-08-03 | United Technologies Corp | Capot avec verrou à taux limité |
US9845708B2 (en) | 2013-01-29 | 2017-12-19 | United Technologies Corporation | Cowl with rate limited lock |
Also Published As
Publication number | Publication date |
---|---|
US20130091825A1 (en) | 2013-04-18 |
WO2011151577A3 (fr) | 2012-09-13 |
FR2960855A1 (fr) | 2011-12-09 |
CA2801400A1 (fr) | 2011-12-08 |
EP2576346A2 (fr) | 2013-04-10 |
US8869506B2 (en) | 2014-10-28 |
CN102939244A (zh) | 2013-02-20 |
RU2012156112A (ru) | 2014-07-20 |
BR112012030428A2 (pt) | 2016-08-09 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2011151577A2 (fr) | Nacelle pour turboréacteur avec dispositif de reprise d'efforts circonférentiels | |
EP2057071B1 (fr) | Systeme de verrouillage pour capot mobile de nacelle | |
EP2577033B1 (fr) | Inverseur de poussée à section de tuyère variable verrouillable | |
EP2932077A1 (fr) | Inverseur de poussée de nacelle et nacelle équipée d'au moins un inverseur | |
CA2379193C (fr) | Systeme de verrouillage synchronise des portes d'un inverseur de poussee | |
EP2193594A2 (fr) | Actionneur lineaire telescopique double action a systeme d'entraînement a moteur unique | |
EP2181378B1 (fr) | Nacelle de turboréacteur, destinée à équiper un aéronef | |
EP2440768A1 (fr) | Dispositif d'inversion de poussée | |
EP2625388A1 (fr) | Inverseur de poussée | |
EP0834651A1 (fr) | Procédé et dispositifs de fermeture des portes d'inverseur de poussée | |
WO2012140368A1 (fr) | Inverseur de poussée pour turboréacteur d'aéronef | |
WO2012131230A1 (fr) | Dispositif de verrouillage à détection mécanique de fermeture et ouverture | |
FR2926537A1 (fr) | Systeme de verrouillage pour structure d'entree d'air d'une nacelle de turboreacteur | |
EP3388657B1 (fr) | Dispositif et procédé de déverouillage d'une nacelle de turboréacteur | |
WO2013182820A1 (fr) | Dispositif de verrouillage/déverrouillage pour capot monobloc d'inverseur de poussée de nacelle de turboréacteur | |
WO2009027590A1 (fr) | Nacelle de turboréacteur, destinée à équiper un aéronef | |
WO2009024469A1 (fr) | Nacelle équipée d'un dispositif de détection de l'état de verrouillage d'un dispositif de verrouillage | |
WO2012095600A1 (fr) | Dispositif de liaison d'un cadre avant à un carter de soufflante | |
WO2014140491A1 (fr) | Dispositif d'inhibition mécanique intégré à une ligne de défense d'un inverseur de poussée | |
FR2957979A1 (fr) | Dispositif d'inversion de poussee | |
EP2179118B1 (fr) | Dispositif de verrouillage | |
FR2939477A1 (fr) | Nacelle de turboreacteur a section de tuyere variable |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 201180027317.9 Country of ref document: CN |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 11726912 Country of ref document: EP Kind code of ref document: A2 |
|
ENP | Entry into the national phase |
Ref document number: 2801400 Country of ref document: CA |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2011726912 Country of ref document: EP |
|
ENP | Entry into the national phase |
Ref document number: 2012156112 Country of ref document: RU Kind code of ref document: A |
|
REG | Reference to national code |
Ref country code: BR Ref legal event code: B01A Ref document number: 112012030428 Country of ref document: BR |
|
ENP | Entry into the national phase |
Ref document number: 112012030428 Country of ref document: BR Kind code of ref document: A2 Effective date: 20121129 |