WO2014033398A1 - Ensemble de maintien de l'interface d'un cadre avant d'une nacelle et d'un carter de turboréacteur - Google Patents
Ensemble de maintien de l'interface d'un cadre avant d'une nacelle et d'un carter de turboréacteur Download PDFInfo
- Publication number
- WO2014033398A1 WO2014033398A1 PCT/FR2013/051969 FR2013051969W WO2014033398A1 WO 2014033398 A1 WO2014033398 A1 WO 2014033398A1 FR 2013051969 W FR2013051969 W FR 2013051969W WO 2014033398 A1 WO2014033398 A1 WO 2014033398A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- handle
- flange
- groove
- assembly according
- locking
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/90—Mounting on supporting structures or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/37—Retaining components in desired mutual position by a press fit connection
Definitions
- the present invention relates to an assembly for maintaining the interface of a turbojet casing and the structure of an inverter of a nacelle surrounding said turbojet engine.
- the present invention also relates to a propulsion assembly comprising such a holding assembly.
- An aircraft is generally driven by a propulsion unit comprising a turbojet engine surrounded by a nacelle.
- the turbojet engine has upstream fan blades driven by a motor.
- Blower blades are surrounded by a housing for mounting said turbojet engine in the nacelle.
- the blower of the turbojet engine essentially consists of a rotary shaft carrying a plurality of blades.
- the blades are surrounded circumferentially by a housing.
- Blower housings are generally machined metal elements.
- the turbojet may be a turbofan engine capable of generating a hot air flow (also called primary flow) from the turbojet engine combustion chamber, and a cold air flow (secondary flow) from the circulating fan. outside the turbojet engine through a channel an nu the ire, also called “vein”, formed between a fairing of the turbojet engine and an inner wall of the nacelle. At the rear of the nacelle, the two primary and secondary streams mix.
- a hot air flow also called primary flow
- secondary flow cold air flow
- This nacelle is generally equipped with a thrust reverser.
- the thrust reverser during the landing of an aircraft improves the braking capacity of the aircraft by redirecting forward at least a portion of the thrust generated by the turbojet engine.
- the inverter obstructs the gas ejection nozzle and directs the ejection flow of the engine towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the engine. the plane.
- a nacelle generally has a structure comprising an air inlet upstream of the engine, a structure median intended to surround the turbojet engine casing, and a downstream structure comprising a fixed internal structure (“IFS”) and a fixed external structure (“OFS”) intended to surround the combustion chamber of the turbojet engine and housing means for inverting the turbojet engine. thrust.
- IFS fixed internal structure
- OFS fixed external structure
- the thrust reverser means are varied and may be in the form of at least one movable cowl, its "thrust reversing cowls", moving in translation thanks to actuators in a direction substantially parallel to an axis longitudinal of the nacelle.
- the structure of the thrust reverser undergoes axial aerodynamic forces q u i t n d d t t to retreat longitudinally the thrust reversal means relative to a turbojet engine.
- the downstream section comprises fixed elements and, in particular, longitudinal beams arranged upstream to a structure.
- fixed outer member comprising a substantially annular assembly called front frame, formed in one or more parts between said longitudinal beams, and intended to be fixed to the periphery of the downstream edge of the fan housing of the engine.
- the structure of the inverter is generally made in two half parts hinged at the top on the pylon, called "D-duct” or “C duct” structure.
- the maintenance between the fan casing and the front frame is formed by a male part, usually carried by the front frame, cooperating in a female part, usually carried by the housing.
- the front frame is connected to the fan casing by fastening means generally of knife / groove type comprising a substantially annular flange, made of u or more parts, integral with the front frame and cooperating with a groove in J or V form, commonly referred to as J-Ring.
- fastening means generally of knife / groove type comprising a substantially annular flange, made of u or more parts, integral with the front frame and cooperating with a groove in J or V form, commonly referred to as J-Ring.
- Such a holding assembly is not adapted to nacelles in which the rear part is able to slide during maintenance operations (so-called O-duct nacelle) towards the rear of the nacelle in a substantially longitudinal direction of the latter. Indeed, in such a nacelle configuration, it should be provided one or more quarters of the downstream section opening laterally so as to move the flange of the grooves and release the front frame of the housing.
- a set for maintaining the interface of the fixed external structure of a nacelle and the turbojet casing comprising:
- said first and second relief elements being configured to be brought into contact with each other;
- two half-rings formed by a wall defining a housing, configured to receive the first and second elements in relief when the housing and the external fixed structure are mounted edge to edge, and stop means configured to maintain the first and second relief elements in the dwelling.
- This holding assembly thus makes it possible to connect, by a connecting flange formed by two half-rings, the downstream end of the casing and the upstream end of the fixed external structure of the downstream structure housing the thrust reversal means.
- the two half-rings can be fixed together by fastening means, which ensures the clamping force and maintenance of the elements in relief.
- the fastening means may comprise locking elements such as a three-point hook lock, one of the half-rings supporting the part of the lock comprising the hook and the other half-ring supporting the part comprising the retaining member of said hook.
- locking elements comprising an actuating handle pivotally mounted on one end of the connecting flange and a connecting rod interposed between the other end of the flange and a portion of the separate handle. of the axis of rotation of this handle.
- Such a device is used to pre-constrain the connecting flange when it is in the closed position.
- the opening of the half-rings of the flange of the season depends on the specific circumferential dimensions of the nacelles on which the locking element and the flange are installed.
- the locking elements must be adapted specifically to nacelles with particular circumferential dimensions.
- a problem posed is, therefore, to ensure a fixed position of the connecting flange when it is in the open position, for the same stroke of the handle regardless of circumferential dimensional variations of the nacelle concerned.
- An object of the present invention is to overcome this problem.
- the present invention proposes a support assembly for a front thrust reverser frame at a turbojet engine casing, comprising:
- At least one connecting flange intended to engage with the front frame and the turbojet casing so as to bind them
- a locking system is provided on the fastening flange for locking two ends of the connecting flange together, this system comprising an actuating handle pivotally mounted on one of the ends of the flange and a connecting rod. linkage interposed between the other end of the flange and a portion of the handle distinct from an axis of rotation of this handle.
- the holding assembly is remarkable in that:
- the handle comprises a support provided with a groove and a screw for adjusting the free length of this groove
- the connecting rod comprises an axis capable of pivoting and sliding in the groove so that:
- the axis of the connecting rod abuts at one end of the groove, in the open position of the connecting flange or in the closed position of the connecting flange and, - The axis of the connecting rod abuts against the adjusting screw located at the other end of the groove, respectively in the closed position of the connecting flange or in the open position of the connecting flange.
- the adjusting screw allows to obtain a variable stroke between the two ends of the closure connection flange, depending on the nacelles on which this flange must be adapted.
- the holding assembly of the invention allows, more pl us, to lock and unlock the interface of the housing and the front frame for nacelles of different circumferential dimensions, simply and quickly.
- the holding assembly of the invention comprises one or more of the following optional features considered alone or according to all the possible combinations:
- the handle comprises a handle slidably mounted on the support and comprising a locking element so that:
- the same clearance is always obtained at the opening between the two ends of the connecting flange for the same stroke of the weight regardless of the variations in circumferential dimensions of the corresponding nacelles.
- the locking member comprises a locking finger formed at one end of the handle;
- the blocking element comprises an adjustable wedge formed at one end of the handle;
- the support of the handle is pivotally mounted about a longitudinal axis relative to the end of the flange on which it is fixed;
- the rod is mounted on the other flange end by a ball joint or pivot;
- the adjusting screw is adapted to define a dead stroke of the handle
- the adjusting screw is slidably mounted on the support of the handle, cooperating with a nut mounted on the support of the handle;
- the link rod is of adjustable length, in order to allow to adjust the clearance between the two ends of the connecting flange in the open position;
- the handle is pivotably mounted on one of the flange ends between at least one locked open position and a locked closed position;
- the handle handle comprises a locking bolt adapted to cooperate with two latches secured to one end of the flange, and for locking the handle in its respective opening and closing positions;
- the invention furthermore relates to an aircraft propulsion unit comprising a rboreactant arranged in a cabin, the turbojet comprising fan blades surrounded by a casing mounted edge-to-edge with a front frame of the downstream structure. of the nacelle, said propulsion unit comprising a holding assembly as mentioned above.
- the length of the handle is such that it exceeds the volume of the nacelle when it is in the open position, eliminating the risk that it closes the basket without having properly closed the flange, when maintenance operations.
- FIG. 1 is a longitudinal section of a propulsion system of the invention
- FIG. 2 is a perspective view of an embodiment of a holding assembly between a turbojet casing and a front frame of a rear section of the nacelle of FIG. 1, the holding assembly being in commitment position;
- FIGS. 3 to 6 are sectional views of a locking device of the holding assembly of Figure 2, in different successive steps of closing a connecting flange of said holding assembly;
- FIGS. 7 to 9 are the views of FIGS. 3, 4 and 6 in which part of the locking device of the holding assembly of FIG. 2 has been removed;
- FIGS. 10 and 11 are two sectional views of a first embodiment of a system for adjusting the effective stroke of a flange of the assembly of the assembly of FIG. illustrating two distinct effective strokes, the connecting flange being in the closed position;
- FIGS. 12 and 13 are sectional views of a variant embodiment of the effective stroke control system of FIGS.
- FIG. 14 is a sectional view of an alternative embodiment of an actuating handle of a locking device of the holding assembly of Figure 2;
- FIGS. 15a and 15b are two enlarged views of zone A of FIG.
- FIG. 1 is a schematic representation of a turbojet nacelle 1 which has an axis of revolution or principal longitudinal axis A.
- the nacelle 1 constitutes a substantially tubular housing for a turbojet engine and generally comprises an upstream air inlet section 2, a central section 3 surrounding a fan of the turbojet engine and a downstream section 4 surrounding a combustion chamber of the turbojet engine.
- the upstream section 2 conventionally comprises an air intake lip structure 2a extended by a downstream air intake structure 2b.
- the median section 3 surrounds the fan of the turbojet and has an inner wall formed by a casing 3a of the fan (illustrated in FIG. 2).
- the downstream section 4 may house a thrust reverser device 4b disposed in the extension of an upstream attachment section 4a to the rest of the nacelle, and in particular to the median section 3.
- downstream section 4 it is important to be able to connect the downstream section 4 and the median section 3 in a manner that is uniquely similar to that of the longitudinal section of the nacelle. the downstream section 4.
- the attachment of the downstream section 4 to the middle section 3 is effected by means of a front frame 40 of the downstream section 4 (and in particular ensuring the support of the reversal device of thrust 4b if appropriate) having a substantially annular shape.
- the upstream end of the front frame 40 is configured to be connected to the downstream end of the fan casing 3a.
- the housing 3a and the front frame 40 are said "mounted edge to edge”.
- the attachment of the front frame 40 to the fan casing 3a is ensured by a holding assembly 100 which makes it possible to hold and lock the front frame 40 and the fan casing 27.
- this example of 100% comprises:
- a first embossed element 101 belonging to the upstream end of the front frame 40 (conventionally called "J-ring” due to its substantially J shape having an end return with which a connecting flange 1 10 can come into stacker),
- first 101 and second 102 relievable elements being configured to be brought into contact with each other
- the connecting flange 1 10 is made of at least two flange sectors 1 10a, 1 10b mounted pivotally movable between:
- the flange 1 comprises two flange sectors 1 10a, 1 10b substantially semi-peripheral able to open outwards, by pivoting them about a substantially longitudinal axis P located at the level of a lower end (not shown) of said flange sector
- the flange sectors 1 10a, 1 10b are advantageously fixed to each other by locking means 200 making it possible to ensure the force of clamping and holding the elements in relief.
- These locking means 200 can provide a lock facilitating precise control of the kinematics of opening and closing of the connecting flange 1 10.
- the two flange sectors 1 10 a, 1 10 b can advantageously meet in the 12 o position relative to the nacelle in front view, as illustrated in FIGS. 6 and 9.
- the locking means 200 of said flange sectors 1 10a, 1 10b are located in this position 12h.
- These locking means 200 are of the three-point type comprising, first and foremost, a control lever mu and an actuating handle 210 pivotally mounted on one of the free ends 1 1 1 b of the first sector. 1 10b of the flange of laison 1 10 and a connecting rod 220 interposed between one of the free ends 1 1 1 a of the second connecting flange sector 1 10a and the handle 210.
- the left sector in Figure 1 10b supports the handle portion 210
- the right flange sector 1 10a supports the portion comprising the connecting rod 220.
- This actuating handle 210 is mounted rotatably between several positions:
- the open locked position of the actuating handle 210 makes it possible to avoid the bridging of the connecting flange 1 1 0 during the rotation insofar as the handle is stable in this determined position.
- the actuating handle 210 comprises a support 21 1 pivotally mounted by a longitudinal axis 212 on a stirrup 1 12 mounted at the free end 1 1 1b of the left sector 1 10b of the connecting flange 1 10 and a sleeve 213 slidably mounted along the support.
- stirrup 1 12 is disposed on the "upper" surface of the corresponding flange sector 1, 10b, namely the furthest away from the interface of the fan casing 3a and the front frame 40. .
- the handle 213 is provided at its end facing the support 21 1 with a locking bolt 214 adapted to cooperate with a plurality of trigger locks 13 distributed over the outer surface of the stirrup 1. 12 sol idaire sector 1 10b flange, to maintain the handle 210 in its respective positions of opening and closing.
- These triggers 1 13 each comprise a notch 1 13 in which the bolt 214 is housed according to the degree of opening of the handle 210.
- two tumblers 1 13 are provided on the stirrup 1 1 2 and arranged in the locked locked and locked open position of the handle 210.
- the distance between the two triggers 1 13 defines the angular travel allowed for the handle 210 between its different open and closed positions.
- the bolt 214 may or may not cooperate with the striker 1 13 corresponding to the degree of opening of the desired handle 210.
- the sleeve 213 has a retracted position on the support 21 1 d a n s l s e l l e p e n 214 214 engages a n s e n g e ch 1 13 and a deployed position in which the bolt 214 is disengaged and free of the corresponding trigger 13.
- the cooperation between the locking bolt 214 and triggers 1 13 makes it possible for the handle 210 when it is opened or closed to have two fixed positions, namely a locked open position by locking the bolt 214 in the trigger. 1 13 corresponding and a locked fixed position closed by the same cooperation of the bolt and a trigger.
- the locking means 200 comprise the connecting rod 220, of adjustable length, interposed between the second 1a 10a sector of the flange 1 10 and a portion of the handle 210 distinct from the axis of rotation 212 of this handle 210.
- the link rod 220 adjustable to regulate the clearance between the two ends of the l ison flange in the open position.
- This rod 220 is provided with a first end articulated on a stirrup 1 14 secured to the second right sector 1 10a of the connecting flange 1 10.
- This bielle 220 is mounted in laison patella or simple pivot, depending on the type of nacelle and the location of the link in question, on a point of attachment of the stirrup 1 14.
- the rod 220 comprises a male part 221 adapted to cooperate with a retaining member 215 located on the support
- the female portion is defined by a through guide lumen 215 formed of a curvilinear groove 215 on the handle support.
- the maie portion is defined by an axis 221 formed of a pin adapted to pivot and slide in the groove 215.
- the pin 221 is slidably mounted in the groove 215 of the handle and articulated on a different axis of the pivot axis of the handle.
- connection between the groove 215 for guiding the handle 210 and the pin 221 of the connecting rod 220 allows an angular displacement of the handle 210 relative to the connecting rod 220.
- This deflection 220 corresponds to the game defined in both directions of the direction of the handle 210 by the length between the two ends of the groove 215.
- any additional angular displacement of the handle towards one of its positions causes a displacement of the connecting rod 220 which subjects to compression or traction efforts the two sectors 110a, 100b and, where appropriate, their approximation or their removal.
- the holding assembly 100 comprises an adjustment system 300 of the effective stroke of the two flange sectors 110a, 110b during their closing / opening, as illustrated, in a first embodiment, in FIGS. 10 and 11. and, in a second embodiment, in Figures 12 and 13.
- This adjustment system 300 comprises a screw 310 of adjustment slidably mounted on the support 211 of the handle 210 and adapted to cooperate with the groove 215 curvilinear of the support 211.
- This screw 310 cooperates with a nut 311 housed in a housing 211a formed on the support 211 and immobile in translation in this housing 211a.
- the free length of the groove 215 is adjusted by acting as a stop, at one or the other end of the groove 215, to the displacement of the pin 221 in the groove 215.
- the nut 310 and the corresponding screw are mounted at one end of the groove 215 while, in the second embodiment illustrated in FIGS. Figures 12 and 13, the nut 310 and the corresponding screw are mounted at the opposite end of the groove 215.
- the dead stroke of the handle 210 and the deflection of the handle 210 that is authorized relative to the connecting rod 220 are adjusted and defined.
- This maximum dead stroke corresponds to the length between the two opposite ends of the groove 215.
- the screw 310 is in the so-called retracted position on the support 21 1, that is to say that its free end intended to cooperate with the pin 221 is placed in line with the end of the guide groove 215. closer to the nut 31 1.
- This stroke corresponds to blocking, therefore, the pin 221 against the end of the groove 215 farthest to the nut 31 1.
- the adjustment system 300 of the dead stroke of the handle 210 makes it possible to determine the effective stroke of the two sectors 1 10a, 1 10b of flange 1 10 during their opening or closing.
- the dead center m axi ma l of the po ized is adapted to allow a minimum stroke between sectors 1 10a, 1 10b of flange.
- the minimum dead stroke is adapted to allow maximum travel between flange sectors 1 10a, 1 10b flange.
- the adjustment system 300 of the dead stroke of the handle 210 makes it possible to adjust the preload of the two flange sectors 110a, 110b, the definition of this precharge making it possible to act on the clearance J between the two ends of the two sectors. flange when closing and locking the connecting flange 110.
- the adjustment system 300 of the dead stroke of the handle 210 also allows this clearance J to be variable between the two ends of the two flange sectors when closing and the locking of the connecting flange.
- the adjustment of the precharge by the second embodiment of the adjustment system 300 of the dead stroke can be improved by the presence of the connecting rod 220.
- This clearance J is a transverse clearance, namely along an axis perpendicular to the longitudinal axis A of the nacelle, after clamping the two sectors 110a, 110b of flange 110.
- This clearance J makes it possible to take into account the manufacturing tolerances of the raised elements 101, 102 of the front frame 40 and of the fan casing 3a to maintain and guarantee the holding force of the two flange sectors 110 between them.
- This adjustable game thus adapts to the different configurations of nacelle in which the locking means 200 can be installed.
- the handle 213 of the handle 210 comprises, at its end where the bolt 214 is formed. , a locking finger 216 adapted to lock the shaft 221 of the connecting rod 220 at one end of the guide groove 215, furthest from the fixing of the adjusting screw 310 on the support 211, when the handle 213 is in position. retracted position on the support 211 and the handle 210 in the locked open position.
- the blocking of the shaft 221 of the connecting rod 220 by the finger 216 of the handle 210 in the open position makes it possible to have a fixed clearance between the two sectors 110a, 110b of the connecting flange 110 at the opening for the same stroke of the handle, regardless of circumferential dimensional variations of the corresponding nacelles.
- a locked open position is provided for the two sectors 110a, 110b of the connecting flange 110 in blocking the axis 221 of the connecting rod 220 by the action of the locking finger 216 of the handle 213, without blocking the axis 221 in rotation throughout the kinematic closure.
- the locking finger 216 is shaped as a bent end portion of the handle 213, whose active face in contact with the axis 221 of the connecting rod 220 is tapered.
- the blocking finger 21 6 is replaced by an adjustable blocking wedge 217 mounted flush on a bent end portion of the sleeve 213.
- This blocking wedge 21 7 cooperates with a screw 21 8 whose screwing will determine the degree of sliding out of the bent end portion of the handle 21 3 of the blocking wedge 21 7 and therefore the thickness of the wedge 21 7 , as a function of the adjustment of the effective stroke of the two sectors 1 10a, 1 10b of flange 1 10 when they are closed / opened.
- This blocking wedge 21 7 is particularly used in the second embodiment of the effective stroke adjustment system of the two sectors 10a, 1 10b flange 1 10 during their closure / opening. Furthermore, the length of the handle 213 of the handle 210 is such that it exceeds the volume of the nacelle when the handle 21 0 is in the locked open position and, more particularly, the outer cover 5 of the nacelle, as illustrated in Figure 3.
- a first step 401 with reference to FIGS. 3 and 7, the locking means 200 are open.
- the two sectors 1 10a, 1 10b of flange 1 10 are open towards the outside, in the open position of the connecting flange 1 10.
- a constant clearance J whatever the circumferential dimensions of the nacelles, is defined between the two ends 1 1 1 a, 1 1 1 b of the two sectors 1 10a, 1 10b of flanges.
- the clearance J can be of the order of 20 mm.
- the two sectors 1 10a, 1 10b flange are locked in their open position by blocking the axis 221 of the link rod 220 connecting against one end of the groove 215 by the finger 216 locking the handle
- the handle 210 In this retracted position of the handle 213, the handle 210 is in the open position and locked in this opening position.
- This step can be identified by the projection of the handle 213 of the handle 210 outside the aerodynamic lines of the outer cover 5, as illustrated in FIG.
- the handle 213 is slid towards the outside of the support 21 1, which causes the engagement of the end 214 of the handle 213 of the trigger 13 of the stirrup 1. 14 secured to the sector 1 10a flange 1 10.
- the locking finger 216 of the handle 213 has, moreover, released the pin 221 of the connecting rod 220.
- the angular displacement of the handle 210 causes a sliding of the pin 221 of the connecting rod 220 in the guide groove 215, towards the opposite end of the groove 215 towards the adjusting screw 310.
- the handle 210 is in an intermediate position between its open position and closing, at the end of its dead stroke.
- the axis 221 of the biel 220 is at the opposite end of the groove 215, abutting against the free end of the adjusting screw 310.
- the effective stroke of flange sectors 10a, 10b and the dead travel of the weight have been previously determined by adjusting a predetermined sliding of the adjusting screw 310. on the support 21 1, this to adjust the free length of the groove 215 guide.
- the handle 210 is, therefore, in the locked closed position.
- the axis 221 of the connecting rod is always held in abutment against the free end of the adjusting screw 310 of the stroke adjustment system 300.
- This second embodiment offers the advantage, relative to the first embodiment, of optimally controlling the closing force of the connecting flange 1, insofar as once it is in the closed position, the axis 221 of the connecting rod 220 remains unchanged.
- the present invention is not limited to the embodiments described above, and any other variants of the holding assembly could be considered.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Steering Devices For Bicycles And Motorcycles (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2015109921A RU2015109921A (ru) | 2012-08-27 | 2013-08-26 | Узел для крепления зоны сопряжения передней рамы гондолы к корпусу турбореактивного двигателя |
BR112015003926A BR112015003926A2 (pt) | 2012-08-27 | 2013-08-26 | conjunto para suportar uma armação frontal de um reversor de empuxo para uma carcaça de motor turbojato e conjunto de propulsão compreendendo um motor turbojato. |
CA2882318A CA2882318C (fr) | 2012-08-27 | 2013-08-26 | Ensemble de maintien de l'interface d'un cadre avant d'une nacelle et d'un carter de turboreacteur |
CN201380044912.2A CN104603401B (zh) | 2012-08-27 | 2013-08-26 | 用于固定机舱前框架和涡轮喷气发动机外壳界面的组件 |
EP13762189.2A EP2888453A1 (fr) | 2012-08-27 | 2013-08-26 | Ensemble de maintien de l'interface d'un cadre avant d'une nacelle et d'un carter de turboréacteur |
US14/630,837 US9388769B2 (en) | 2012-08-27 | 2015-02-25 | Assembly for holding the interface of a front frame of a nacelle and a turbojet engine casing |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1257992A FR2994711B1 (fr) | 2012-08-27 | 2012-08-27 | Ensemble de maintien de l'interface d'un cadre avant d'une nacelle et d'un carter de turboreacteur |
FR12/57992 | 2012-08-27 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/630,837 Continuation US9388769B2 (en) | 2012-08-27 | 2015-02-25 | Assembly for holding the interface of a front frame of a nacelle and a turbojet engine casing |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014033398A1 true WO2014033398A1 (fr) | 2014-03-06 |
Family
ID=47088953
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2013/051969 WO2014033398A1 (fr) | 2012-08-27 | 2013-08-26 | Ensemble de maintien de l'interface d'un cadre avant d'une nacelle et d'un carter de turboréacteur |
Country Status (8)
Country | Link |
---|---|
US (1) | US9388769B2 (fr) |
EP (1) | EP2888453A1 (fr) |
CN (1) | CN104603401B (fr) |
BR (1) | BR112015003926A2 (fr) |
CA (1) | CA2882318C (fr) |
FR (1) | FR2994711B1 (fr) |
RU (1) | RU2015109921A (fr) |
WO (1) | WO2014033398A1 (fr) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3010050B1 (fr) * | 2013-09-04 | 2017-03-31 | Snecma | Structure de liaison moteur-nacelle a secteurs de virole articules |
FR3081444B1 (fr) * | 2018-05-25 | 2020-05-29 | Safran Nacelles | Dispositif de verrouillage pour aeronef |
US11268406B2 (en) | 2019-08-12 | 2022-03-08 | The Boeing Company | Movement-limiting device for a turbine engine and associated method |
FR3119648B1 (fr) * | 2021-02-05 | 2023-01-27 | Safran Nacelles | Inverseur de poussée comprenant des grilles et des capots mobiles assemblés par embrèvement |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB594198A (en) * | 1945-06-28 | 1947-11-05 | Napier & Son Ltd | Improvements in or relating to fasteners for movable panels and like parts |
EP1752648A2 (fr) * | 2005-08-10 | 2007-02-14 | United Technologies Corporation | Tuyère de propulsion ayant une encoche courbée dans une entretoise de volet |
FR2952615A1 (fr) * | 2009-11-18 | 2011-05-20 | Aircelle Sa | Ensemble de maintien de l'interface d'une structure externe fixe d'une nacelle et d'un carter de turboreacteur |
EP2434193A2 (fr) * | 2010-09-24 | 2012-03-28 | Rolls-Royce plc | Ensemble de pince et verrou circonférentiel |
WO2012095600A1 (fr) * | 2011-01-14 | 2012-07-19 | Aircelle | Dispositif de liaison d'un cadre avant à un carter de soufflante |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3347578A (en) * | 1964-11-18 | 1967-10-17 | Boeing Co | Flush-type safety latch |
US4951973A (en) * | 1988-03-17 | 1990-08-28 | General Electric Company | Joint connection for annular flanges |
US5076514A (en) * | 1990-08-03 | 1991-12-31 | The Boeing Company | Apparatus for latching two parts together |
FR2920133B1 (fr) * | 2007-08-20 | 2009-10-30 | Aircelle Sa | Nacelle de turboreacteur, destinee a equiper un aeronef |
FR2960855A1 (fr) * | 2010-06-03 | 2011-12-09 | Aircelle Sa | Nacelle pour turboreacteur avec dispositif de reprise d'efforts circonferentiels |
-
2012
- 2012-08-27 FR FR1257992A patent/FR2994711B1/fr active Active
-
2013
- 2013-08-26 CA CA2882318A patent/CA2882318C/fr not_active Expired - Fee Related
- 2013-08-26 CN CN201380044912.2A patent/CN104603401B/zh active Active
- 2013-08-26 RU RU2015109921A patent/RU2015109921A/ru not_active Application Discontinuation
- 2013-08-26 BR BR112015003926A patent/BR112015003926A2/pt not_active IP Right Cessation
- 2013-08-26 WO PCT/FR2013/051969 patent/WO2014033398A1/fr active Application Filing
- 2013-08-26 EP EP13762189.2A patent/EP2888453A1/fr not_active Withdrawn
-
2015
- 2015-02-25 US US14/630,837 patent/US9388769B2/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB594198A (en) * | 1945-06-28 | 1947-11-05 | Napier & Son Ltd | Improvements in or relating to fasteners for movable panels and like parts |
EP1752648A2 (fr) * | 2005-08-10 | 2007-02-14 | United Technologies Corporation | Tuyère de propulsion ayant une encoche courbée dans une entretoise de volet |
FR2952615A1 (fr) * | 2009-11-18 | 2011-05-20 | Aircelle Sa | Ensemble de maintien de l'interface d'une structure externe fixe d'une nacelle et d'un carter de turboreacteur |
EP2434193A2 (fr) * | 2010-09-24 | 2012-03-28 | Rolls-Royce plc | Ensemble de pince et verrou circonférentiel |
WO2012095600A1 (fr) * | 2011-01-14 | 2012-07-19 | Aircelle | Dispositif de liaison d'un cadre avant à un carter de soufflante |
Also Published As
Publication number | Publication date |
---|---|
BR112015003926A2 (pt) | 2017-07-04 |
CN104603401A (zh) | 2015-05-06 |
CA2882318A1 (fr) | 2014-03-06 |
RU2015109921A (ru) | 2016-10-20 |
FR2994711A1 (fr) | 2014-02-28 |
US20150167586A1 (en) | 2015-06-18 |
CA2882318C (fr) | 2016-01-19 |
FR2994711B1 (fr) | 2014-08-08 |
US9388769B2 (en) | 2016-07-12 |
EP2888453A1 (fr) | 2015-07-01 |
CN104603401B (zh) | 2016-04-13 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2222470C (fr) | Dispositif de liaison d'un inverseur de poussee a un turbomoteur | |
EP2577033B1 (fr) | Inverseur de poussée à section de tuyère variable verrouillable | |
EP2665911B1 (fr) | Inverseur de poussée pour turboréacteur d'aéronef à nombre de verrous réduit | |
FR2929998A1 (fr) | Nacelle de turboreacteur a double flux | |
WO2014091140A1 (fr) | Inverseur de poussée de nacelle et nacelle équipée d'au moins un inverseur | |
WO2013186475A1 (fr) | Inverseur de poussée à grilles rétractables | |
EP2181378B1 (fr) | Nacelle de turboréacteur, destinée à équiper un aéronef | |
EP3388657B1 (fr) | Dispositif et procédé de déverouillage d'une nacelle de turboréacteur | |
FR3037039A1 (fr) | Dispositif de verrouillage de capots pivotants d’un inverseur de poussee | |
EP2888453A1 (fr) | Ensemble de maintien de l'interface d'un cadre avant d'une nacelle et d'un carter de turboréacteur | |
EP2178760B1 (fr) | Nacelle de turboréacteur, destinée à équiper un aéronef | |
EP3303811B1 (fr) | Inverseur de poussée pour nacelle de turboréacteur d'aéronef | |
WO2012095600A1 (fr) | Dispositif de liaison d'un cadre avant à un carter de soufflante | |
FR3006716A1 (fr) | Inverseur de poussee a volet de blocage articule par embiellage trois points | |
EP2188178B1 (fr) | Nacelle de turboréacteur, destinée à équiper un aéronef | |
WO2014072655A1 (fr) | Nacelle pour turboreacteur comprenant un ensemble unitaire mobile le long d'un ensemble de guidage | |
WO2012035223A1 (fr) | Dispositif de verrouillage/déverrouillage pour inverseur de poussée à capot coulissant et à tuyère adaptative pour nacelle de moteur d'aéronef | |
WO2010066957A1 (fr) | Nacelle de turboreacteur a section de tuyere variable | |
FR2993932A1 (fr) | Dispositif d'entrainement de volets notamment pour tuyere adaptative | |
FR3027066A1 (fr) | Inverseur de poussee pour nacelle de turboreacteur d'aeronef et nacelle associee |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 13762189 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 2882318 Country of ref document: CA |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
REEP | Request for entry into the european phase |
Ref document number: 2013762189 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2013762189 Country of ref document: EP |
|
ENP | Entry into the national phase |
Ref document number: 2015109921 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: 112015003926 Country of ref document: BR |
|
ENP | Entry into the national phase |
Ref document number: 112015003926 Country of ref document: BR Kind code of ref document: A2 Effective date: 20150224 |