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
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D29/00—Power-plant nacelles, fairings, or cowlings
  • B64D29/08—Inspection panels for power plants
• • 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
  • F02K1/78—Other construction of jet pipes
  • F02K1/80—Couplings or connections
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T137/00—Fluid handling
  • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Definitions

• the present invention relates to a rear assembly nacelle jet engine, and a nacelle equipped with such a set.
• An airplane is driven by one or more turbojet engines each housed in a nacelle.
• a nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, an intermediate assembly intended to surround a fan of the turbojet engine, a rear assembly that can incorporate thrust reverser means and intended to surround the combustion chamber and all or part of the compressor and turbine shelves of the turbojet, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
• the modern nacelles are intended to house a turbojet engine capable of generating on the one hand a hot air flow (also called primary flow) from the combustion chamber of the turbojet, and on the other hand a cold air flow (Secondary flow) from the blower and circulating outside the turbojet through an annular passage, also called vein, formed between a structu re i nterne defining a fairing of the turbojet engine and an inner wall of the nacelle.
• the two air flows are ejected from the turbojet engine from the rear of the nacelle.
• the thrust reversal means allow, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forwards at least a portion of the thrust generated by the turbojet engine.
• the inverter generally obstructs the cold flow vein and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.
• the means implemented to achieve this reorientation of the cold flow vary according to the type of inverter.
• spindle means that the internal structure has a central zone of greater diameter than its upstream and downstream ends.
• O-duct commonly used in the field of aircraft nacelles, means that the member concerned (in this case, the downstream part of the internal structure) extends over substantially the entire circumference of the generator. gas from the plane.
• an "O-duct" member can only allow access to the gas generator by axial sliding.
• an internal structure "O-duct" may abut on it when its neck l isme from its operating position to its maintenance position: the downstream displacement of the internal structure is limited, so that it is possible to access certain organs of the gas generator that providing access hatches on this body.
• the structure of the downstream engine bonnet is dependent on the outer movable cowling of the nacelle and in particular in the case of a nacelle equipped with a thrust reverser device.
• the outer cover being attached to the inner cover by means of drive rods of the thrust reverser of the thrust reverser, their respective kinematics are intimately related.
• the locking in the lower part of the turbojet hoods requires to have cutouts and complex hooking interfaces.
• the present invention is thus particularly intended to provide a nacelle rear assembly of the aforementioned type to overcome these disadvantages, including obtaining an isostatic mounting, while maintaining easy access to the turbojet engine during maintenance operations.
• the present invention relates to a turbojet engine nacelle rear assembly, comprising, on the one hand, an external cover, and on the other hand, an internal spindle-shaped structure, said internal structure comprising at least one downstream portion and an upstream portion each mounted movably between an operating position in which they are connected, thus covering the gas generator of said turbojet engine and defining an annular cold air duct with said outer cover, and at least one maintenance position in which they are separated from each other so as to allow access to the gas generator, the downstream portion being movably mounted by axial sliding while the upstream portion is movable by opening towards the outside of at least one door , the downstream part and the upstream part being equipped with connecting means able to cooperate with each other, this assembly being characterized in that at least one of the downstream parts and t upstream part is equipped with articulation means having a movement in at least one direction so as to allow maneuvering and operation of the relevant part without constraints.
• the whole is free from the risk of hyperstatism.
• the upstream portion and the downstream portion are movable in their maintenance position independently of one another.
• each of the upstream and downstream parts is equipped with articulation means having a movement in at least one direction so as to allow maneuvering and operation of each concerned part without constraints.
• the downstream portion and the upstream portion are equipped with connecting means adapted to cooperate with each other, this assembly being characterized in that the means of the iaison are of the knife / throat type. comprising at least one ring at least partially peripheral knife forming and adapted to cooperate with a corresponding groove of the other part.
• the upstream part is also equipped with connection means able to cooperate with corresponding connecting means of a fan casing of the turbojet engine.
• connection means will conventionally be of the knife / throat type.
• the upstream portion comprises at least one locking means of the door.
• the latch is disposed substantially in the same plane as articulation hinges of the upstream part.
• the upstream portion comprises hinge hinges preferably arranged in the upper part, that is to say near an interface with an attachment pylon.
• the upstream portion is equipped with at least one hinge on either side of a pylon, the two hinges being connected by a connecting rod.
• the connecting rod is without contact with surrounding structures when the upstream portion is in the operating position.
• the downstream portion is associated with at least one guide means mounted with a vertical deflection, in particular upstream of said downstream portion.
• downstream portion is associated with at least one guide means mounted with a rotary deflection, in particular downstream of said downstream portion.
• the rotational movement may in particular be in a substantially longitudinal plane and / or in a transverse plane.
• downstream portion is associated with at least one guide means having an angle of inclination with respect to a substantially longitudinal axis of the assembly.
• the means for guiding and articulating at least one of the downstream and upstream parts have an operating configuration in which they have a minimum clearance and a maintenance configuration in which they have an enlarged clearance.
• the guide assembly allows an upstream clearance of the downstream part.
• the means for guiding and articulating at least one of the downstream and upstream parts are equipped with centering means, in particular of the pawn type.
• the upstream portion and the downstream portion are equipped with at least one keying means, in particular in the form of a heel.
• a visual indication of non-locking of the downstream cover by the upstream cover is placed in a visible area by the maintenance personnel.
• the present invention also relates to an aircraft nacelle, characterized in that it is equipped with an assembly according to any one of the preceding claims.
• FIG. 1 is a schematic representation of a rear assembly according to the invention.
• FIG. 2 is a diagrammatic view in longitudinal section of the assembly of FIG. 1.
• FIG. 3 is an enlarged partial view of the junction between the upstream portion of the assembly of Figure 2 and a fan casing.
• FIG. 4 is an enlarged partial view of the junction between the upstream part of the assembly of Figure 2 and the downstream part of the same set.
• FIG. 5 is an enlarged partial view in transverse section taken at an articulation of the upstream part of the assembly of FIG. 1.
• FIG. 6 is a diagrammatic representation of a means for guiding the rear part of the assembly of FIG. 1.
• FIG. 7 is a schematic representation of a foolproof means in the form of a heel.
• FIG. 8 is a schematic representation of a centering means equipping the heel of Figure 7.
• FIGS 1 to 4 show various views of a rear assembly 1 for a turbojet engine 2 comprising in particular a gas generator 3 and, upstream thereof, a fan which can be seen a housing 5.
• the front frame 7 is structuring, that is to say that it can support the weight of the entire turbojet engine 1, as well as the thrust and counter-thrust forces generated. by this turbojet.
• the present invention is not limited to the presence of such a frame before structuring, and that any conventional fastening means of the turbojet engine 1 to the pylon 9 is also within the scope of the present invention.
• An internal structure January 1 nacelle comprising an upstream portion 1 3 and a downstream portion 1 5, forms a fairing for the gas generator 3 and is connected to the pylon 9 by means allowing appropriate kinematics which will be described later.
• the internal structure 1 1 defines, with u n ca external pot (not shown), an annular cold air stream, adapted to allow the circulation of cold air generated by the fan downstream of the nacelle.
• the outer cover may include thrust reverser means, typically having a plurality of flaps that can be actuated by connecting rods during sliding of the outer cover relative to the internal structure January 1.
• thrust reverser typically having a plurality of flaps that can be actuated by connecting rods during sliding of the outer cover relative to the internal structure January 1.
• the operation of a thrust reverser is not the object of the present application and is well known to those skilled in the art.
• the internal structure 1 1 is connected to the fan casing 5 via the upstream part 1 3 by a knife-like connection 25a / groove 27b (FIGS. 2 and 3) respectively belonging to the upstream part 13 and 5.
• a knife-like connection 25a / groove 27b (FIGS. 2 and 3) respectively belonging to the upstream part 13 and 5.
• the reverse arrangement or other known connection means are possible.
• the contiguous edges of the upstream part 1 3 and of the downstream part 1 5 of the internal structure 1 1 comprise complementary connecting means of the groove type 27b and the knife type 25b.
• the downstream part 1 5 is slidably mounted on the pylon 9 by means of rail and slide means represented symbolically by the reference 31 visible in FIG. 2.
• This upstream portion 13 comprises in fact two half-doors able to open outwards, that is to say away from the gas generator 3, by pivoting about the respective axes d isposés way substantially parallel to the rail and glissier means 31 is in the upper part of the upstream structure integrating a portion of the side surface of the pylon (island) is at the island interface and barrel.
• the two doors are closed and locked by means of locking means which will be arranged preferably in the lower part (that is to say opposite the pylon 9) and preferably placed in the same place.
• locking means which will be arranged preferably in the lower part (that is to say opposite the pylon 9) and preferably placed in the same place.
• the locking also aims to ensure a pretension of the doors around locking rims to allow optimal structural strength.
• upstream part 13 differs from that of the downstream part 1 5, the latter being of the "O-DUCT" type as defined in the preamble of the description, that is to say extending over practically the entire circumference of the gas generator 3.
• the two doors of the upstream part 13 of the internal structure 1 1 are opened by opening outwards.
• the opening of the two doors makes it possible to remove the knives 27b from those doors of the complementary groove 25b formed in the downstream part 15 of the internal structure 1 1.
• downstream part 1 5 can be run downstream of the gas generator 3, the two doors remaining in the open position. In this maintenance configuration, it is therefore easy to access the downstream zone of the gas generator 3, as well as a large part of its upstream zone.
• the means of articulation of at least one of the downstream parts 1 5 and upstream 1 3 have a movement according to the m insunedi rectio ndemani e to pe rm be uneman ⁇ u vre and an operation of the concerned without constraint.
• FIGS. 5 and 6 illustrate exemplary embodiments of these articulation means for the upstream portion 13 and the downstream portion 15, respectively.
• FIG. 5 represents an example of articulation of a door of the upstream part 13 by a hinge 131.
• the articulation hinges 131 are located near the pylon 9.
• the example shown shows an upstream portion 1 3 at a block 1 32 interface with the tower 9.
• This island 132 interface is an extension of an upstream part panel to extend the pylon 9 up to the cylindrical part, also called barrel, and to ensure the aerodynamic continuity.
• the upstream portion 1 3 will not present an island and will consist only of the barrel.
• hinge line is not necessary parallel to a substantially longitudinal axis of the nacelle.
• the hinges 1 31 must provide a joint without constraints.
• Figure 5 shows an arrangement that allows a refocusing and maintenance of the structure 1 1 relative to the tower 9 by the installation of a connecting rod 1 33 through said pylon 9 to connect two hinges 131 on either side of it.
• a game 1 34 is also formed between the upstream cover 1 3 and the tower 9. This game 134 is however minimized to ensure performance optimal aerodynamics. A not shown seal will isolate the internal part of the hood 1 3 of the flow vein of the secondary flow. A clearance 135 is also provided between the connecting rod and the connecting rod passage in the pylon 9.
• connecting rod 133 serves as a connecting rod support 133.
• downstream part 15 is articulated so as to allow operation without constraint.
• the downstream part 15 is centered and positioned by a strapping formed with the upstream part 1 3.
• the manufacturing tolerances associated with the differences in expansion of the components and movements, as well as the reduced distance between a first point of attachment of the slide on the tower 9 and the attachment of the downstream part 15 of the internal structure 1 1 on the upstream part 1 3 make it necessary to arrange a specific constitution of the sliding system.
• the system 151 slides 152 allows guidance of the downstream cover without constraint.
• FIG. 6 makes it possible not to induce stress in the structures in use.
• the axial positioning is given by a slider of the downstream part 1 5 on the corresponding slide 1 52 of the guide system 1 5, while the vertical positioning is given by the centering of the strapping interface carried by the upstream portion 1 3 at the junction of its junction with the downstream portion 15.
• the guide assembly 151, upstream is mounted free on at least one support integrated in a fixed structure of the aircraft such as the tower 9 .
• the guide assembly 151 will be attached to the pylon 9 upstream through upstream supports 1 55 forming eyelets and having an oblong opening for a vertical movement of the slide support 151.
• the guide assembly 151 Downstream, the guide assembly 151 is advantageously connected by a central point 154 to the fixed structure of the aircraft (pylon 9). This point allows a good deflection around its pivot point. Through a ball joint, an additional degree of deflection in a vertical transverse plane is permitted.
• Figure 6 shows yokes 1 55, 1 54 carried by the pylon.
• Link arms between the two slides can be added in particular vis-à-vis the slide structure carried by the downstream engine cover to resume all efforts to open the structure.
• the guide system 151 may also have a non-parallel configuration with the longitudinal axis of the nacelle and have an angle therewith.
• the support 151 may remain non-parallel once the upstream portion 1 3 open or be in a substantially parallel position once the upstream portion 13 open. This makes it possible to further limit the stresses likely to be exerted during the flow of the downstream part 15.
• the guiding system in the active position, the guiding system must generally comprise a minimal clearance said functional between the rail and the slide while in the open position, a larger game will facilitate the introduction and sliding.
• the guiding assembly 1 51 must preferentially allow the internal structure 1 1 to be advanced in order to provide access to the disassembly of a primary window in the event of need and to ensure the same ent of components carried by the internal structure 11 1 and that will enter into interference with the primary shell; -
• the guide assembly 151 may be equipped with removable end stops limit stops.
• At least one heel 28 is carried by the grooved ring forming the groove 27.
• the length of the heel 28 depends on the distance considered between the two parts 13, 15 of the internal structure 1 1 as detectable at the eye and for which it is no longer necessary to provide a foolproof.
• the heel 28 may be continuous, or discrete, local or multiple.
• FIG. 8 An exemplary embodiment is shown in Figure 8 in the form of a positioning pin 30 adapted to cooperate with a corresponding bore 29 formed in the keying heel 28.
• the invention may also be advantageously completed by means, including mechanical, visual indication of closure and locking.

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

Priority Applications (7)

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

Country Status (9)

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Citations (4)

Family Cites Families (13)

• 2009
  • 2009-12-07 FR FR0905903A patent/FR2953490B1/fr not_active Expired - Fee Related
• 2010
  • 2010-11-26 CN CN2010800555950A patent/CN102648128A/zh active Pending
  • 2010-11-26 WO PCT/FR2010/052546 patent/WO2011070266A1/fr active Application Filing
  • 2010-11-26 EP EP20100801603 patent/EP2509870B1/fr active Active
  • 2010-11-26 ES ES10801603.1T patent/ES2503562T3/es active Active
  • 2010-11-26 US US13/514,554 patent/US20120247571A1/en not_active Abandoned
  • 2010-11-26 RU RU2012127242/11A patent/RU2545558C2/ru not_active IP Right Cessation
  • 2010-11-26 BR BR112012012078A patent/BR112012012078A2/pt not_active IP Right Cessation
  • 2010-11-26 CA CA 2780299 patent/CA2780299A1/fr not_active Abandoned

Patent Citations (4)

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