WO2015092313A1 - Turbojet engine nacelle comprising a secure lock for the rear half-portions - Google Patents

Turbojet engine nacelle comprising a secure lock for the rear half-portions Download PDF

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Publication number
WO2015092313A1
WO2015092313A1 PCT/FR2014/053444 FR2014053444W WO2015092313A1 WO 2015092313 A1 WO2015092313 A1 WO 2015092313A1 FR 2014053444 W FR2014053444 W FR 2014053444W WO 2015092313 A1 WO2015092313 A1 WO 2015092313A1
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WO
WIPO (PCT)
Prior art keywords
covers
handle
turbojet engine
engine nacelle
lock
Prior art date
Application number
PCT/FR2014/053444
Other languages
French (fr)
Inventor
Frédéric ZOONEKYNDT
Patrick BOILEAU
Cédric RENAULT
Matthieu Morel
Original Assignee
Aircelle
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aircelle filed Critical Aircelle
Publication of WO2015092313A1 publication Critical patent/WO2015092313A1/en

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Classifications

    • 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

Definitions

  • Turbojet engine nacelle comprising a secure rear half-lock
  • the present invention relates to an aircraft nacelle receiving a turbojet, comprising a locking latch between two rear half-parts, and hoods opening in front of these parts.
  • the motorization assemblies for the aircraft generally comprise a nacelle forming a generally circular outer envelope, comprising inside a turbojet arranged along the longitudinal axis of this nacelle.
  • the turbojet engine receives fresh air from the upstream or front side, and rejects on the downstream or rear side hot gases from the combustion of fuel, which give a certain thrust.
  • the turbofan engines have around the engine fan blades generating a significant secondary flow of cold air along an annular vein passing between the engine and the nacelle, which adds a high thrust in normal operation giving a direct jet.
  • Some nacelles comprise a thrust reversal system which closes at least part of the annular cold air duct, and rejects the secondary flow forward forming an inverted jet which generates a braking counter-pressure of the aircraft .
  • nacelle One type of nacelle known, presented in particular by the document FR-A1-2920144, comprises two half-covers covering the median section surrounding the secondary flow blower, hereinafter referred to as front cowls, comprising a hinge having a longitudinal axis located in the upper part, so as to allow opening of the lower parts of these covers for maintenance operations.
  • the rear of the nacelle receiving a thrust reverser has two rear half-parts that connect to the lower point. Locks arranged at the bottom of the rear parts, realize a tangential clamping between these two parts to keep them in the closed position.
  • the upstream lock may comprise a control handle having a locking member, which prevents the closing of the covers before as long as this handle is not in its closed position, or that the locking member is not in its locked position.
  • this lock does not provide security in all cases of maintenance that may occur.
  • the present invention is intended to avoid these disadvantages of the prior art.
  • a turbojet engine nacelle comprising two rear half-sections arranged downstream of front half-covers, the two rear parts and the two covers closing one against the other along the same axial junction plane.
  • latch arranged at the junction between the rear parts, on the upstream side, and tangentially clamping between these two parts comprises a pivoting handle in a transverse plane, characterized in that the lock is locked and the front covers closed , the handle is fully fitted in a transverse outer cutout which extends on the two covers, except for a recess formed at its free end which comes below one of the covers.
  • turbojet engine nacelle according to the invention may furthermore comprise one or more of the following characteristics, which may be combined with one another.
  • the cutting of the covers is at the edge of the rear parts.
  • the latch being open, the cutting of the covers is provided to pass without risk of contact the movable elements of the latch as the handle or a closing hook, when operating these covers. This avoids accidental closing of the handle during a fall of a hood.
  • recess can form a substantially flat surface, disposed parallel to the surface of the cap covering it.
  • a game is interposed between the recess of the handle and the cover covering it, and between the cutting of the covers and this handle. This avoids any risk of friction and wear.
  • the lock comprises a safety hook pivotally attached to the handle, which locks automatically when the complete closure of the handle. This hook completes the latch lock security.
  • the safety hook may include a pusher on the handle, which remains visible by cutting the covers when they are closed. We can thus the hood being closed, to monitor the good locking of the lock.
  • FIG. 1 is an overall view in axial section of a turbojet engine nacelle
  • FIG. 2 is an external view of a latch of a nacelle according to the invention.
  • FIG. 3 is a cross-sectional view of the closed lock
  • FIG. 1 shows a nacelle containing a turbojet engine 10 supported by a pylon 4 fixed under the wing of an aircraft.
  • the nacelle comprises a front section 6 comprising a profiled air inlet, a central section 2 surrounding the cold air blower 14, and a rear section 8comterrorism flaps of the thrust reverser.
  • the nacelle forms an external profiling of the annular vein 12 guiding the flow of cold air, and an aerodynamic outer fairing.
  • the central section 2 comprises two outer cover caps, arranged symmetrically with respect to a vertical axial plane, which can open laterally by pivoting about a hinge comprising a longitudinal axis arranged in the upper part.
  • the rear section has two rear lateral parts, which are closed one on the other following the same plane of axial symmetry.
  • Figure 2 is a bottom view of the nacelle having at the top the two covers before 20, 22 and down the two rear portions 24, 26, these covers and these closed rear portions being connected in the plane of symmetry P.
  • the two rear portions 24, 26 are clamped one on the other in a tangential direction by several locks, including a lock having a handle 28, operating in a transverse plane.
  • a lock having a handle 28, operating in a transverse plane.
  • the handle 28 is fitly arranged in a transverse outer cutout extending on these two covers, at the limit of the rear portions 24, 26.
  • the free end of the handle 28 which tilts in the maneuver, shown on the right of the figure, has a recess which shifts slightly towards the axis of the nacelle, to come below the right front cover 20.
  • Figures 3 and 4 show the handle 28 fixed by pivots to the left rear part 26, acting by a rocker 34 on a locking lever comprising a main hook 30 to take a loop at the end of a rod 32 attached to the right rear 24.
  • a safety hook 36 pivotally attached to the handle 28 is automatically take by the action of a spring loop of the rod 32.
  • To open the handle 28 it is necessary press on a pusher 38 of the safety hook 36 located in the outer plane of the handle 28, to press on to release the hook and release the handle which can then rock.
  • the front covers 20, 22 come just below the rear portions 24, 26.
  • the free end of the handle 28 has the recess 40 which comes inside the right front cover 20, forming a substantially flat surface parallel to this cover with a game, so as to avoid any contact between this cover and this handle. There is likewise a clearance between the closed handle 28 and the edges of the cut.
  • This front cover 20 being closed, it can no longer open the handle 28, or close it if it is open.
  • the handle 28 being held open by a spring, and the main hook 30 being tilted downwards protruding radially outwardly from the rear parts 24, 26 supporting it, the cutting of the covers 20, 22 allows in any case when their closures or their falls do not abut on an element of the lock, including the handle and the hook.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A turbojet engine nacelle comprising a secure lock for the rear half-portions. A turbojet engine nacelle comprising two rear half-portions (24, 26) arranged downstream from front half-covers (20, 22), the two rear portions and the two covers closing against each other in a same axial junction plane (P), a lock provided at the junction between the two rear portions (24, 26), on the upstream side, and tangentially clamping these two portions together, comprises a manoeuvring handle (28) that pivots in a transverse plane, characterised in that, with the lock locked and the front covers (20, 22) closed, the handle (28) is fully fitted into a transverse external cutout that extends over the two covers, apart from a shoulder formed at the free end of same that is below one of the covers (20).

Description

Nacelle de turboréacteur comprenant un verrou de demi-parties arrière sécurisé  Turbojet engine nacelle comprising a secure rear half-lock
La présente invention concerne une nacelle d'aéronef recevant un turboréacteur, comportant un verrou de fermeture entre deux demi-parties arrière, et des capots ouvrant en avant de ces parties. The present invention relates to an aircraft nacelle receiving a turbojet, comprising a locking latch between two rear half-parts, and hoods opening in front of these parts.
Les ensembles de motorisation pour les aéronefs comportent généralement une nacelle formant une enveloppe extérieure globalement circulaire, comprenant à l'intérieur un turboréacteur disposé suivant l'axe longitudinal de cette nacelle. Le turboréacteur reçoit de l'air frais venant du côté amont ou avant, et rejette du côté aval ou arrière les gaz chauds issus de la combustion du carburant, qui donnent une certaine poussée.  The motorization assemblies for the aircraft generally comprise a nacelle forming a generally circular outer envelope, comprising inside a turbojet arranged along the longitudinal axis of this nacelle. The turbojet engine receives fresh air from the upstream or front side, and rejects on the downstream or rear side hot gases from the combustion of fuel, which give a certain thrust.
Les turboréacteurs à double flux présentent autour du moteur des aubes de soufflante générant un flux secondaire important d'air froid le long d'une veine annulaire passant entre ce moteur et la nacelle, qui ajoute une poussée élevée en fonctionnement normal donnant un jet direct.  The turbofan engines have around the engine fan blades generating a significant secondary flow of cold air along an annular vein passing between the engine and the nacelle, which adds a high thrust in normal operation giving a direct jet.
Certaines nacelles comportent un système d'inversion de poussée qui ferme au moins en partie la veine annulaire d'air froid, et rejette le flux secondaire vers l'avant en formant un jet inversé qui génère une contre- poussée de freinage de l'aéronef.  Some nacelles comprise a thrust reversal system which closes at least part of the annular cold air duct, and rejects the secondary flow forward forming an inverted jet which generates a braking counter-pressure of the aircraft .
Un type de nacelle connu, présentée notamment par le document FR-A1 - 2920144, comporte deux demi-capots recouvrant la section médiane entourant la soufflante de flux secondaire, appelés par la suite capots avant, comportant une charnière disposant d'un axe longitudinal situé en partie supérieure, de manière à permettre une ouverture des parties inférieures de ces capots pour des opérations de maintenance.  One type of nacelle known, presented in particular by the document FR-A1-2920144, comprises two half-covers covering the median section surrounding the secondary flow blower, hereinafter referred to as front cowls, comprising a hinge having a longitudinal axis located in the upper part, so as to allow opening of the lower parts of these covers for maintenance operations.
L'arrière de la nacelle recevant un inverseur de poussée, comporte deux demi-parties arrière qui se raccordent au point inférieur. Des verrous disposés en bas des parties arrière, réalisent un serrage tangentiel entre ces deux parties afin de les maintenir en position fermée.  The rear of the nacelle receiving a thrust reverser, has two rear half-parts that connect to the lower point. Locks arranged at the bottom of the rear parts, realize a tangential clamping between these two parts to keep them in the closed position.
Le verrou amont peut comporter une poignée de commande disposant d'un organe de blocage, qui empêche la fermeture des capots avant tant que cette poignée n'est pas dans sa position de fermeture, ou que l'organe de blocage n'est pas dans sa position verrouillée. The upstream lock may comprise a control handle having a locking member, which prevents the closing of the covers before as long as this handle is not in its closed position, or that the locking member is not in its locked position.
Toutefois ce verrou n'assure pas une sécurité dans tous les cas de maintenance qui peuvent se présenter. Notamment pour assurer cette sécurité, il est souhaitable que la poignée ne soit pas cachée en position non verrouillée sous un capot avant, ne puisse pas être refermée par un capot lors de sa fermeture ou de sa chute, ne puisse pas être déverrouillée lorsque ce capot est fermé, et que son déverrouillage puisse toujours être détecté facilement.  However, this lock does not provide security in all cases of maintenance that may occur. In particular to ensure this security, it is desirable that the handle is not hidden in the unlocked position under a front cover, can not be closed by a cover when closed or dropped, can not be unlocked when the cover is closed, and that unlocking can still be easily detected.
De plus en cas de chute du capot avant sur le verrou ouvert, ce capot ne doit pas venir percuter la poignée pour éviter d'avoir à disposer des renforcements de protection sur le capot ajoutant une masse et un encombrement.  In addition, in the event of a fall of the front cover on the open lock, this cover must not hit the handle to avoid having to have protective reinforcements on the cover adding a mass and a bulk.
La présente invention a notamment pour but d'éviter ces inconvénients de la technique antérieure.  The present invention is intended to avoid these disadvantages of the prior art.
Elle propose à cet effet une nacelle de turboréacteur comprenant deux demi-parties arrière disposées en aval de demi-capots avant, les deux parties arrière et les deux capots se refermant l'un contre l'autre suivant un même plan axial de jonction, un verrou disposé au niveau de la jonction entre les parties arrière, du côté amont, et réalisant un serrage tangentiel entre ces deux parties, comporte une poignée de manœuvre pivotant dans un plan transversal, caractérisée en ce que le verrou étant verrouillé et les capots avant fermés, la poignée est entièrement ajustée dans une découpeextérieure transversale qui se prolonge sur les deux capots, à l'exception d'un décrochement formé à son extrémité libre qui vient en dessous d'un des capots.  To this end, it proposes a turbojet engine nacelle comprising two rear half-sections arranged downstream of front half-covers, the two rear parts and the two covers closing one against the other along the same axial junction plane. latch arranged at the junction between the rear parts, on the upstream side, and tangentially clamping between these two parts, comprises a pivoting handle in a transverse plane, characterized in that the lock is locked and the front covers closed , the handle is fully fitted in a transverse outer cutout which extends on the two covers, except for a recess formed at its free end which comes below one of the covers.
Un avantage de cette nacelle est que le verrou étant ouvert, les capots avant en chutant ne peuvent percuter la poignée qui passe dans la découpe de ces capots. En évitant un choc sur la poignée, on n'a alors pas besoin de renfort spécifique sur le capot pour le protéger. De plus avec le décrochement de la poignée recouvert par un capot, on ne peut pas ouvrir cette poignée le capot étant fermé. La nacelle de turboréacteur selon l'invention peut comporter de plus une ou plusieurs des caractéristiques suivantes, qui peuvent être combinées entre elles. An advantage of this platform is that the latch being open, the front hoods falling can not hit the handle that passes in the cutout of these covers. By avoiding a shock on the handle, we do not need specific reinforcement on the hood to protect it. Moreover with the recess of the handle covered by a hood, we can not open this handle with the hood closed. The turbojet engine nacelle according to the invention may furthermore comprise one or more of the following characteristics, which may be combined with one another.
Avantageusement, la découpe des capots se trouve à la limite des parties arrière.  Advantageously, the cutting of the covers is at the edge of the rear parts.
Avantageusement le verrou étant ouvert, la découpe des capots est prévue pour laisser passer sans risque de contact les éléments mobiles du verrou comme la poignée ou un crochet de fermeture, lors de la manœuvre de ces capots. On évite ainsi une fermeture accidentelle de la poignée lors d'une chute d'un capot.  Advantageously, the latch being open, the cutting of the covers is provided to pass without risk of contact the movable elements of the latch as the handle or a closing hook, when operating these covers. This avoids accidental closing of the handle during a fall of a hood.
En particulière décrochement peut former une surface sensiblement plane, disposée parallèlement à la surface du capot le recouvrant.  In particular recess can form a substantially flat surface, disposed parallel to the surface of the cap covering it.
Avantageusement, un jeu est interposé entre le décrochement de la poignée et le capot le recouvrant, ainsi qu'entre la découpe des capots et cette poignée. On évite ainsi tout risque de frottement et d'usure.  Advantageously, a game is interposed between the recess of the handle and the cover covering it, and between the cutting of the covers and this handle. This avoids any risk of friction and wear.
Avantageusement, le verrou comporte un crochet de sécurité fixé de manière pivotante sur la poignée, qui se verrouille automatiquement lors de la fermeture complète de cette poignée. Ce crochet complète la sécurité de fermeture du verrou.  Advantageously, the lock comprises a safety hook pivotally attached to the handle, which locks automatically when the complete closure of the handle. This hook completes the latch lock security.
Dans ce cas, le crochet de sécurité peut comporter un poussoir se trouvant sur la poignée, qui reste visible par la découpe des capots quand ils sont fermés. On peut ainsi le capot étant fermé, surveiller le bon verrouillage du verrou.  In this case, the safety hook may include a pusher on the handle, which remains visible by cutting the covers when they are closed. We can thus the hood being closed, to monitor the good locking of the lock.
L'invention sera mieux comprise et d'autres caractéristiques et avantages apparaîtront plus clairement à la lecture de la description ci-après donnée à titre d'exemple, en référence aux dessins annexés dans lesquels :  The invention will be better understood and other features and advantages will emerge more clearly on reading the following description given by way of example, with reference to the appended drawings in which:
- la figure 1 est vue une d'ensemble en coupe axiale d'une nacelle de turboréacteur ;  - Figure 1 is an overall view in axial section of a turbojet engine nacelle;
- la figure 2 est une vue extérieure d'un verrou d'une nacelle selon l'invention ;  - Figure 2 is an external view of a latch of a nacelle according to the invention;
- la figure 3 est une vue en coupe transversale de ce verrou fermé ; et - Figure 3 is a cross-sectional view of the closed lock; and
- la figure 4 est une vue en coupe transversale de ce verrou ouvert. La figure 1 présente une nacelle contenant un turboréacteur 10 supporté par un pylône 4 fixé sous l'aile d'un aéronef. La nacelle comporte une section avant 6 comprenant une entrée d'air profilée, une section centrale 2 entourant la soufflante d'air froid 14, et une section arrière 8comprenant des volets de l'inverseur de poussée. La nacelle forme un profilage externe de la veine annulaire 12 guidant le flux d'air froid, et un carénage extérieur aérodynamique. - Figure 4 is a cross-sectional view of this open lock. FIG. 1 shows a nacelle containing a turbojet engine 10 supported by a pylon 4 fixed under the wing of an aircraft. The nacelle comprises a front section 6 comprising a profiled air inlet, a central section 2 surrounding the cold air blower 14, and a rear section 8comprenant flaps of the thrust reverser. The nacelle forms an external profiling of the annular vein 12 guiding the flow of cold air, and an aerodynamic outer fairing.
La section centrale 2 comporte deux capots de recouvrement extérieur, disposés de manière symétrique par rapport à un plan axial vertical, qui peuvent s'ouvrir latéralement en pivotant autour d'une charnière comprenant un axe longitudinal disposé en partie supérieure.  The central section 2 comprises two outer cover caps, arranged symmetrically with respect to a vertical axial plane, which can open laterally by pivoting about a hinge comprising a longitudinal axis arranged in the upper part.
La section arrière comporte deux parties latéralesarrière, qui se referment l'une sur l'autre suivant le même plan de symétrie axiale.  The rear section has two rear lateral parts, which are closed one on the other following the same plane of axial symmetry.
La figure 2 est une vue de dessous de la nacelle présentant en haut les deux capots avant 20, 22 et en bas les deux parties arrière 24, 26, ces capots et ces parties arrière fermés se raccordant suivant le plan de symétrie P.  Figure 2 is a bottom view of the nacelle having at the top the two covers before 20, 22 and down the two rear portions 24, 26, these covers and these closed rear portions being connected in the plane of symmetry P.
Les deux parties arrière 24, 26 sont serrées l'une sur l'autre suivant une direction tangentielle par plusieurs verrous, dont un verrou comportant une poignée 28, se manœuvrant dans un plan transversal. Quand ce verrou est verrouillé et les capots avant 20, 22 fermés, la poignée 28 est disposée de manière ajustée dans une découpe extérieure transversale se prolongeant sur ces deux capots, à la limite des parties arrière 24, 26.  The two rear portions 24, 26 are clamped one on the other in a tangential direction by several locks, including a lock having a handle 28, operating in a transverse plane. When this lock is locked and the front covers 20, 22 closed, the handle 28 is fitly arranged in a transverse outer cutout extending on these two covers, at the limit of the rear portions 24, 26.
L'extrémité libre de la poignée 28 qui bascule dans la manœuvre, présentée à droite de la figure, comporte un décrochement qui la décale légèrement vers l'axe de la nacelle, pour venir en dessous du capot avant droit 20.  The free end of the handle 28 which tilts in the maneuver, shown on the right of the figure, has a recess which shifts slightly towards the axis of the nacelle, to come below the right front cover 20.
Les figures 3 et 4 présentent la poignée 28 fixée par des pivots à la partie arrière gauche 26, agissant par un basculeur 34 sur un levier de verrouillage comprenant un crochet principal 30 venant prendre une boucle se trouvant à l'extrémité d'une tige 32 fixée à la partie arrière droite 24.  Figures 3 and 4 show the handle 28 fixed by pivots to the left rear part 26, acting by a rocker 34 on a locking lever comprising a main hook 30 to take a loop at the end of a rod 32 attached to the right rear 24.
Une fois la poignée 28 entièrement refermée, un crochet de sécurité 36 fixé de manière pivotante sur la poignée 28, vient automatiquement prendre par l'action d'un ressort la boucle de la tige 32. Pour ouvrir la poignée 28, il faut presser sur un poussoir 38 du crochet de sécurité 36 se trouvant dans le plan extérieur de la poignée 28, afin d'appuyer dessus pour dégager ce crochet et libérer cette poignée qui peut alors basculer. Once the handle 28 completely closed, a safety hook 36 pivotally attached to the handle 28, is automatically take by the action of a spring loop of the rod 32. To open the handle 28, it is necessary press on a pusher 38 of the safety hook 36 located in the outer plane of the handle 28, to press on to release the hook and release the handle which can then rock.
Les capots avant 20, 22 viennent juste en-dessous des parties arrière 24, 26. La surface extérieure de la poignée 28 ajustée dans la découpe des capots 24, 26, vient sensiblement au niveau de la surface de ces capots afin d'obtenir une continuité aérodynamique de la surface extérieure de la nacelle.  The front covers 20, 22 come just below the rear portions 24, 26. The outer surface of the handle 28 fitted into the cutout of the covers 24, 26, comes substantially at the surface of these covers to obtain a aerodynamic continuity of the outer surface of the nacelle.
L'extrémité libre de la poignée 28 présente le décrochement 40 qui vient à l'intérieur du capot avant droit 20, en formant une surface sensiblement plane parallèle à ce capot avec un jeu, de manière à ne risquer aucun contact entre ce capot et cette poignée. On a de même un jeu entre la poignée fermée 28 et les bords de la découpe.  The free end of the handle 28 has the recess 40 which comes inside the right front cover 20, forming a substantially flat surface parallel to this cover with a game, so as to avoid any contact between this cover and this handle. There is likewise a clearance between the closed handle 28 and the edges of the cut.
Ce capot avant 20 étant fermé, on ne peut alors plus ouvrir la poignée 28, ni la fermer si elle est ouverte.  This front cover 20 being closed, it can no longer open the handle 28, or close it if it is open.
Par ailleurs la poignée 28 étant maintenue ouverte par un ressort, et le crochet principal 30 étant basculé vers le bas en dépassant radialement vers l'extérieur des parties arrière 24, 26 le supportant, la découpe des capots 20, 22 permet dans tous les cas lors de leurs fermetures ou leurs chutes de ne pas buter sur un élément du verrou, notamment sur la poignée et le crochet.  Furthermore, the handle 28 being held open by a spring, and the main hook 30 being tilted downwards protruding radially outwardly from the rear parts 24, 26 supporting it, the cutting of the covers 20, 22 allows in any case when their closures or their falls do not abut on an element of the lock, including the handle and the hook.
On n'a alors pas besoin de disposer des renforts sur les capots avant 20, We do not need to have reinforcements on the covers before 20,
22 au niveau du verrou pour éviter de les détériorer en cas de choc, ce qui permet de réduire les masses et les encombrements. De plus grâce aux découpes des capots avant 20, 22, une fermeture de ces capots ne peut pas accrocher la poignée 28 de manière accidentelle, en fermant alors le verrou. 22 at the lock to prevent damage in case of impact, which reduces the masses and congestion. Moreover thanks to the cutouts of the front covers 20, 22, a closing of these covers can not hang the handle 28 accidentally, then closing the lock.
On notera que grâce à la découpe des capots avant 20, 22 laissant apparaître la face extérieure de la poignée 28 au travers de ces découpes, on peut surveiller la bonne position du poussoir 38 du crochet de sécurité 36 afin de s'assurer que le verrou est complètement fermé.  Note that by cutting the front covers 20, 22 revealing the outer face of the handle 28 through these cutouts, one can monitor the correct position of the pusher 38 of the safety hook 36 to ensure that the lock is completely closed.
On obtient une solution économique et peu encombrante, qui sans ajouter de masse, permet d'assurer de manière simple la sécurité dans tous les cas de fonctionnement.  An economical and space-saving solution is obtained which, without adding any mass, makes it possible in a simple manner to ensure safety in all cases of operation.

Claims

REVENDICATIONS
1 - Nacelle de turboréacteur comprenant deux demi-parties arrière (24, 26) disposées en aval de demi-capots avant (20, 22), les deux parties arrière et les deux capots se refermant l'un contre l'autre suivant un même plan axial de jonction (P), un verrou disposé au niveau de la jonction entre les deux parties arrière (24, 26), du côté amont, et réalisant un serrage tangentiel entre ces deux parties, comporte une poignée de manœuvre (28) pivotant dans un plan transversal, caractérisée en ce que le verrou étant verrouillé et les capots avant (20, 22) fermés, la poignée (28) est entièrement ajustée dans une découpeextérieure transversale qui se prolonge sur les deux capots, à l'exception d'un décrochement formé à son extrémité libre (40) qui vient en dessous d'un des capots (20). 1 - turbojet engine nacelle comprising two rear half-parts (24, 26) arranged downstream of front half-covers (20, 22), the two rear parts and the two covers closing one against the other following a same axial junction plane (P), a latch disposed at the junction between the two rear portions (24, 26), on the upstream side, and tangentially clamping between these two parts, comprises a pivoting operating handle (28) in a transverse plane, characterized in that the lock being locked and the front covers (20, 22) closed, the handle (28) is fully adjusted in a transverse outer cutout which extends on the two covers, except for a recess formed at its free end (40) which comes below one of the covers (20).
2 - Nacelle de turboréacteur selon la revendication 1 , caractérisée en ce que la découpe des capots (20, 22) se trouve à la limite des parties arrière (24, 2 - turbojet engine nacelle according to claim 1, characterized in that the cutout of the covers (20, 22) is at the limit of the rear parts (24,
26). 26).
3 - Nacelle de turboréacteur selon la revendication 1 ou 2, caractérisée en ce que le verrou étant ouvert, la découpe des capots (20, 22) est prévue pour laisser passer sans risque de contact les éléments mobiles du verrou comme la poignée (28) ou un crochet de fermeture (30), lors de la manœuvre de ces capots.  3 - turbojet engine nacelle according to claim 1 or 2, characterized in that the latch being open, the cutting of the covers (20, 22) is provided to pass without risk of contact the movable elements of the latch as the handle (28) or a closing hook (30), during the maneuvering of these covers.
4 - Nacelle de turboréacteur selon l'une quelconque des revendications précédentes, caractérisée en ce que le décrochement (40) forme une surface sensiblement plane, disposée parallèlement à la surface du capot le recouvrant (20).  4 - turbojet engine nacelle according to any one of the preceding claims, characterized in that the recess (40) forms a substantially flat surface, arranged parallel to the surface of the cap covering (20).
5 - Nacelle de turboréacteur selon l'une quelconque des revendications précédentes, caractérisée en ce qu'un jeu est interposé entre le décrochement (40) de la poignée (28) et le capot le recouvrant (20), ainsi qu'entre la découpe des capots (20, 22) et cette poignée.  5 - turbojet engine nacelle according to any one of the preceding claims, characterized in that a game is interposed between the recess (40) of the handle (28) and the cover covering (20), and between the cut hoods (20, 22) and this handle.
6 - Nacelle de turboréacteur selon l'une quelconque des revendications précédentes, caractérisée en ce que le verrou comporte un crochet de sécurité (36) fixé de manière pivotante sur la poignée (28), qui se verrouille automatiquement lors de la fermeture complète de cette poignée. 6 - turbojet engine nacelle according to any one of the preceding claims, characterized in that the lock comprises a safety hook (36) pivotally attached to the handle (28), which locks automatically when the handle is fully closed.
7 - Nacelle de turboréacteur selon la revendication 6, caractérisée en ce que le crochet de sécurité (36) comporte un poussoir (38) se trouvant sur la poignée (28), qui reste visiblepar la découpe des capots (20, 22) quand ils sont fermés.  7 - turbojet engine nacelle according to claim 6, characterized in that the safety hook (36) comprises a pusher (38) located on the handle (28), which remains visible by cutting the covers (20, 22) when they are closed.
PCT/FR2014/053444 2013-12-20 2014-12-19 Turbojet engine nacelle comprising a secure lock for the rear half-portions WO2015092313A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1363279A FR3015435B1 (en) 2013-12-20 2013-12-20 TURBO AIRBOAT COMPRISING SECURED BACK HALF PARTS LATCH
FR1363279 2013-12-20

Publications (1)

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WO2015092313A1 true WO2015092313A1 (en) 2015-06-25

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PCT/FR2014/053444 WO2015092313A1 (en) 2013-12-20 2014-12-19 Turbojet engine nacelle comprising a secure lock for the rear half-portions

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FR (1) FR3015435B1 (en)
WO (1) WO2015092313A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3081837A1 (en) * 2018-06-05 2019-12-06 Airbus Operations AIRCRAFT TURBOMACHINE ASSEMBLY WITH ARTICULATED HOOD
US20230184012A1 (en) * 2021-11-12 2023-06-15 Rohr, Inc. Aircraft safety latch

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6666408B1 (en) * 1999-11-10 2003-12-23 Aerospatiale Matra Airbus Closure fault indicator, particularly for an aircraft engine pod cowl
US20040104583A1 (en) * 2001-11-27 2004-06-03 Alain Porte Device for indicating incorrect closure of locking means located between two fan cowlings of an aircraft engine nacelle
FR2920144A1 (en) 2007-08-20 2009-02-27 Aircelle Sa NACELLE EQUIPPED WITH A DEVICE FOR DETECTING THE LATCHING STATE OF A LATCHING DEVICE

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6666408B1 (en) * 1999-11-10 2003-12-23 Aerospatiale Matra Airbus Closure fault indicator, particularly for an aircraft engine pod cowl
US20040104583A1 (en) * 2001-11-27 2004-06-03 Alain Porte Device for indicating incorrect closure of locking means located between two fan cowlings of an aircraft engine nacelle
FR2920144A1 (en) 2007-08-20 2009-02-27 Aircelle Sa NACELLE EQUIPPED WITH A DEVICE FOR DETECTING THE LATCHING STATE OF A LATCHING DEVICE

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3081837A1 (en) * 2018-06-05 2019-12-06 Airbus Operations AIRCRAFT TURBOMACHINE ASSEMBLY WITH ARTICULATED HOOD
US11242159B2 (en) 2018-06-05 2022-02-08 Airbus Operations Sas Aircraft turbomachine assembly comprising an articulated cowl
US20230184012A1 (en) * 2021-11-12 2023-06-15 Rohr, Inc. Aircraft safety latch

Also Published As

Publication number Publication date
FR3015435B1 (en) 2016-02-05
FR3015435A1 (en) 2015-06-26

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