Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
• • 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
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
  • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
  • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• • 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
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the present invention relates to the field of nacelles for aircraft engines and, more specifically, to a rear nacelle assembly for an aircraft engine.
• an aircraft engine which is generally of the turbojet type, is placed inside a nacelle which, among other functions:
• the nacelle has, generally, a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section intended to surround the combustion chamber of the turbojet engine and housing, the where appropriate, means for reversing thrust.
• Modern nacelles are intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow) from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular passage, also called vein, formed between a shroud 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 downstream section of a nacelle for such a turbojet engine generally has a fixed external structure, called the Outer Fixed Structure (OFS), and a concentric fixed internal structure, called the Inner Fixed Structure (I FS), surrounding a downstream section of the turbojet engine. sheltering the turbojet engine gas generator.
• OFS Outer Fixed Structure
• I FS Inner Fixed Structure
• the internal and external fixed structures define the vein for channeling the flow of cold air flowing outside the turbojet engine.
• the means implemented to achieve the reorientation of the cold air flow include cold air flow deflection grids and a movable cover movable between, d on the one hand, an extended position in which it opens in the nacelle a passage for the flow of cold air deviated, and secondly, a retracted position in which it closes this passage, the hood having only a simple sliding function to discover or cover these grids.
• this thrust reverser device comprises two half-hemi-cylindrical cowls, mounted so that, in particular during maintenance operations, they can be opened "in butterfly” by pivoting about a longitudinal hinge line, close to a suspension pylon through which the nacelle is connected to the wing or the fuselage of the aircraft.
• Such a structure is called C-duct.
• the IFS can also be formed of a C-duct structure and deploys "in butterfly" by pivoting about a longitudinal hinge line, close to the suspension pylon between a working position and a maitenance position to give access to the gas generator during the operations of maitenance.
• part of N FS and the half-covers must be open at the same time butterfly, during a maintenance operation.
• Each of the two half-covers is, therefore, slidably mounted on a longitudinal support half-beam, said beam 12h, pivotally mounted on the pylon, the rotational movement of each half-beam on the pylon ensuring the pivoting of each half. hood with respect to this pylon.
• each half-beam will be provided with rails intended to cooperate with slides mounted on the half-covers to ensure the translation of the half-cover concerned and a plurality of hinge clevises capable of allowing the articulation of the half-beam on the associated pylon.
• the C-duct type structures have the advantage of providing easy access to the engine after unlocking systems for holding the half-covers and pivoting them.
• Another disadvantage is the simultaneous opening of the IFS and the hood which forces the I FS and the hood to be directly connected to them in the upper part of the hood.
• the opening of the cover in operation or during maintenance operations, can be effected by sliding along guide rails that can be arranged on either side of the suspension pylon, the support beams present. at 12h and 6h in C-duct structures can therefore be deleted.
• At least a portion of the internal structure can, for its part, be equally sliding or pivotable along an axis parallel to the axis of sliding of the cover during maintenance operations.
• a nacelle structure offers great flexibility to the nacelle, which makes it more sensitive to deformation.
• the present invention aims to alleviate the above-mentioned disadvantages.
• An object of the invention is to provide a rear nacelle assembly whose fastening system of the components of the assembly reduces the mass of the nacelle.
• Another object of the invention is to provide a rear nacelle assembly for maintenance of the turbojet easy, fast and simple to implement.
• Another object of the present invention is to optimize the maintenance time.
• a rear nacelle turbojet engine comprising at least: an internal structure, intended to surround a downstream part of the turbojet engine, said internal structure being rotatable between a working position in which it forms the downstream fairing of the turbojet engine and defines an annular cold air duct with a hood, and a maintenance position in which it deviates from the downstream part of the turbojet,
• said thrust reversing cowl concentric with said internal structure, said cowl being slidable between an open position giving off airflow deflection grates and a closing position covering said airflow deflection grates;
• said cover being further movable in rotation between a working position in which it defines the annular cold air duct with said internal structure, and a maintenance position in which it deviates from the downstream part of the turbojet,
• this assembly being remarkable in that the cover is mounted on the pylon by a pivot connection sliding about a main axis and the internal structure is mounted on the pylon by a pivot connection about said main axis.
• the rear nacelle turbojet engine also facilitates maintenance operations on the turbojet engine.
• turbojet engine nacelle rear assembly taken alone or in combination:
• the assembly comprises a guiding system in translation and in rotation of the cover comprising at least one rail capable of sliding in a slide, the rail being mounted on the same side and the slide being mounted directly or indirectly on the pylon of the suspension, or vice versa;
• the slide or the rail, if any, is provided on a section fixed to the pylon forming a base of the pylon or on the pylon;
• the main axis is the longitudinal axis of the slideway;
• the assembly comprises a system for guiding the internal structure in rotation, comprising means allowing the pivot connection of the internal structure, connecting the internal structure to the slide of the guiding system in translation and in rotation of the cover, the internal structure being operable in its maintenance position by pivoting around said slide;
• each slide is configured to accommodate one or more of these hooks and prohibit their translation along the corresponding slide;
• the rotation guide system of the internal structure further comprises blocking blocks of the internal structure mounted on the tower;
• the assembly comprises means for simultaneously rotating the internal structure and the cover outwardly around said slideway when the cover has reached an intermediate position between its closed position and its open position;
• a retaining rod supports each rail and connects it to a longitudinal frame formed between internal and external parts of the cover, this rod being able to be straight or bent;
• the cover and the internal structure are formed respectively of semi-hemi-cylindrical half-covers and half-parts, the movements of the half-covers and half-parts on either side of the pylon are symmetrical with respect to a longitudinal median plane of the nacelle the axes of the pivot links, on either side of the pylon being parallel to each other;
• the rear assembly further comprises a rail-slide guide system, in the lower part of the nacelle, connecting each half-part and the corresponding half-cover.
• each half-cover, each half-cover, the deflection grids and half-part of the corresponding internal structure are integral in rotation;
• the cover comprises means for guiding the flow deflection grids in translation
• the rear assembly further comprises means for actuating the cover comprising two actuators disposed in the upper part of the cover on either side of the suspension pylon in the extension of the guide rails;
• the cover actuating means further comprises an actuator disposed in the lower part of the cover, housed in a connecting island connecting each half of the internal structure to the corresponding half-cover;
• said lower actuator is carried by only one of the two half-parts of the internal structure.
• the rear assembly further comprises means for anti-jamming rails in the corresponding slides;
• said anti-jamming means comprise a bail located in the corresponding slideway, in which the rail is placed, said gutter being rotatable about the longitudinal axis of the slideway and locked in translation in the slideway.
• the invention further relates to a nacelle comprising a rear assembly as mentioned above.
• the nacelle comprises a fan casing in which an airflow deflection edge is provided at its downstream end.
• FIGS. 1a to 1c are perspective views of a turbojet engine nacelle having a rear assembly according to the invention comprising a movable cowl of the "C-duct" type in position respectively of closing, intermediate opening and maintenance of the turbojet engine;
• FIGS. 2a and 2b are perspective views of an internal structure of a nacelle rear assembly according to the invention, respectively, in the maintenance position and work;
• FIGS. 3a and 3b are partial perspective views of a nacelle rear assembly according to the invention, respectively, in the working position and maintenance in a version where the inner cover and the outer cover are connected;
• FIGS. 4a and 4b are perspective views of a mounting of aerodynamic sections on a suspension pylon, respectively before and after rotation relative to this pylon in a version where the inner cover and the outer cover are independent;
• FIGS. 5a and 5b are cross-sectional views of the connection between a half-cover and the pylon of the nacelle rear assembly according to the invention, in part top of the nacelle, respectively when the hood is in the working position and in the maintenance position;
• FIGS. 6 and 8a are perspective views of the connection of Figure 5a but for the other half cover, said half cover being invisible in Figure 6;
• FIGS. 7a and 7b are sectional views showing a gutter locking system of the connection between an internal half-structure and the pylon of the nacelle rear assembly according to the invention, in the upper part of the nacelle, respectively when the internal structure is in the working position and in the maintenance position;
• FIG. 8a is a perspective view of the connection, in the upper part of the nacelle, between a half cover and the pylon of the rear nacelle assembly according to the invention
• FIG. 8b is an axial view of the connection, in the upper part of the nacelle, between a half-cover and the pylon of the rear nacelle assembly according to the invention
• FIGS. 9a and 9b are perspective views of the connection between a half-cover and the pylon of the nacelle rear assembly according to the invention, in the upper part of the nacelle, respectively when the cover is in the inverted jet position. and direct jet;
• FIGS. 10a and 10b are perspective views of the connection between a half-cover and the pylon of the nacelle rear assembly according to the invention, in the upper part of the nacelle, respectively when the cover is in the intermediate position of maintenance. and work (direct throw);
• Figures 1 1 and 12 are, respectively, side and bottom views of the nacelle rear assembly according to the invention, a portion of the hood having been removed in Figure 1 1;
• FIGS. 13 and 14a are perspective views of the connection of the internal structure and the cover of the rear nacelle assembly according to the invention, in the lower part of the nacelle;
• FIGS. 14b and 14c illustrate two successive opening stages of the link of FIG. 14a during a maintenance operation
• FIG. 15a to 15e illustrate different successive steps of a removal of a rear nacelle assembly according to the invention.
• identical or similar references designate members or sets of identical or similar members.
• the lower (upper) position of 6 o'clock (respectively 12 o'clock) is usually referred to as a dial of a clock.
• an aircraft propulsion unit 1 comprises a nacelle 2 surrounding a turbojet engine (not shown), both of which have a main longitudinal axis A.
• This nacelle 2 is intended to be attached to a wing of an aircraft (not visible) via a suspension pylon 10 facing upstream of the aircraft.
• the turbojet engine comprises a fan 3 delivering an annular air flow with a primary flow that supplies the motor driving the fan 3 and a secondary flow that is ejected into the atmosphere while providing a significant fraction of the thrust of the aircraft.
• the fan 3 is contained in an outer casing 4 which channels downstream the secondary flow, this housing flat to a median section 6 of the nacelle 2.
• this fan casing 4 provides an aerodynamic deflection edge function.
• any front frame including support deflection grids 32, and means for actuating thrust reverser means, described below, may be deleted.
• the nacelle 2 typically comprises an external structure comprising an upstream air inlet structure 5, a median structure 6 surrounding blades of the fan 3 of the turbojet engine, and a downstream structure 20 that can incorporate the reversing means of the engine. thrust 30.
• the downstream structure 20 comprises an external structure 21 called OFS housing the thrust reversal means 30, this external structure 21 defining with an internal structure 22 comprising a fairing 23 of the engine downstream of the blades of the fan, called IFS 23, concentric , an annular air stream 7 through which the secondary air flow is intended to circulate, as opposed to the hot primary flow generated.
• OFS external structure
• IFS 23 internal structure 22 comprising a fairing 23 of the engine downstream of the blades of the fan, called IFS 23, concentric , an annular air stream 7 through which the secondary air flow is intended to circulate, as opposed to the hot primary flow generated.
• the thrust reverser means 30 comprise, for their part, a cover 31 mounted to be movable in longitudinal translation in a direction substantially parallel to the longitudinal axis A of the nacelle 2 associated with the deflection grilles 32. air flow each having a plurality of deflector vanes and flaps' not visible in these figures) adapted to seal the annular vein 7 during a thrust reversal.
• This cover 31 is able to pass alternately from a closed position (position shown in Figure 1a) in which it ensures the aerodynamic continuity of the external lines of the nacelle 2 with the middle section 6 and covers the grids 32 of the deflection. air flow, to an open position in which it opens a passage in the nacelle 2 by discovering the deflection grids 32 adapted to reorient a portion of the secondary air flow generated by the turbojet engine to the front of the nacelle 2 through the opening thus cleared.
• the position shown in Figure 1 b) is an intermediate position of the cover 31 between its closed position and opening.
• the cover 31 comprises two half-covers 31a, 31b hemicylindrical having, respectively, upper edges 33 mounted on the suspension pylon 10, as shown in Figure 1 c.
• the cover 31 is, in addition, able to move alternately from at least one working position during operation of the aircraft to a maintenance position (shown in Figure 1 c in particular).
• the working positions correspond to the opening and closing positions of the cover 31 described above, taken by the cover 31, respectively in direct or reverse jet.
• the fixing means 40 of each half-cover 31a, 31b on the pylon 10 are configured to allow the pivoting of the half-cover 31a, 31b between the positions work and maintenance around a longitudinal axis parallel to the longitudinal axis A of the nacelle 2, forming a hinge line.
• these fixing means 40 are furthermore configured to allow the half-cover 31 a, 31 b concerned to slide relative to the suspension pylon 10 between the closed and open positions of the cover 31.
• the fastening means 40 will be described with regard to a half-cover 31 a, 31 b only, it being understood that these means are identical on both sides of the pylon 10.
• the fixing means 40 comprise a guide system in translation and in rotation of the half cover 31 a, 31 b consists of a rail assembly 41-slide 42 extending along the longitudinal axis A of the nacelle 2, on either side of the suspension pylon 10.
• the rail-slide assemblies are simple assembly means to implement.
• a longitudinal rail 41 is disposed in the upper part 33 of the corresponding half-cowl 31 a, 31 b intended to be mounted on the suspension pylon 10.
• Each rail 41 is adapted to allow the sliding of the half-cover 31 a, 31 b in a longitudinal slideway 42 extending along the longitudinal axis A of the nacelle 2, formed on the pylon 10.
• each rail 41 is mounted on a longitudinal frame 43, extending along the axis A and connecting the inner portion 310 of the half cover 31 a, 31 b concerned forming part of the vein 7 and the outer portion 31 1 of the latter ensuring the external continuity of the lines of the nacelle 2.
• the associated slideway 42 is mounted on one of the lateral ends of a part 10a integral with the suspension pylon 10.
• This piece 10a is a profile extending along the longitudinal axis A of the nacelle 2, which may have a U-shaped cross-section complementary to that of the pylon 10, this profilel Oa forming the base of the pylon 10.
• This profile 10a is fixed to the pylon 10 by suitable fastening means.
• it may be screwing means.
• the slides 42 may be formed in the branches of the U extending in a plane comprising the longitudinal axis of the nacelle 2.
• each slideway 42 is formed directly on one of the lateral ends of the suspension pylon 10 facing the upper edges 32 of the cover 31, on either side of the pylon 10.
• the guiding slides 42 can be integrated in the pylon 10, without the need for interface components.
• Each slideway 42 located at 12 o'clock, has a longitudinal axis (in dotted lines) extending in a plane parallel to the axis A.
• connection between the pylon 10 and each rail 41 is a sliding pivot-type link axis defined by the longitudinal axis of the slide 42 corresponding.
• Figures 3a and 3b show the half-cover 31b, respectively, before and arpaves rotation about the longitudinal axis of the slide 42, designated in phantom.
• the slideways 42 are in the form of longitudinal grooves extending along the axis A, cylindrical, partially open longitudinally along their circumference for the passage of a retaining rod 44 supporting the associated rail 41 connecting it to the longitudinal frame 43.
• these retaining rods 44 it is possible for these retaining rods 44 to be bent in order to be able to adapt to the various aerodynamic configurations encountered on the nacelles and also to have an orientation of the various stress reactions that are less likely to generate. jamming.
• the cover 31 surrounds NFS 23 concentrically along an axis collinear with the axis A of the nacelle 2.
• IFS 23 is mobile in rotation between a working position (illustrated in FIG. 1 b) in which it serves as a fairing of the downstream part of the turbojet engine and a maintenance position in which it allows access to said downstream portion (illustrated in Figure 1c).
• IFS 23 is thus formed of two half-portions 23a, 23b, of shape adapted to the profile of the downstream turbojet engine and, in a non-limiting example, of hemi-cylindrical shape.
• each half portion 23a, 23b of the IFS 23 is mounted on the pylon 10 so as to open by pivoting outwards (FIGS. and 2a), moving away from the turbojet engine, during maintenance operations, around the guiding system 40 half-covers 31a, 31b corresponding.
• the link between the pylon 10 and each half portion 23a, 23b of the IFS 23 is a pivot-type link axis defined by the longitudinal axis of the slide 42 cooperating with the guide rail 41 of the corresponding half-cover 31 a, 31 b (this axis is shown in dashed lines in Figures 2a and 2b).
• the axis of rotation and translation relative to the connection of a half-cover 31, 31 b and of the pylon 10 is identical to the axis of rotation relative to the connection of the half-portion 23a, 23b and the corresponding pylon 10, namely the longitudinal axis of the slideway 42 of the guide system.
• Each guide system is, therefore, configured so that the sliding axis of each rail 41 forms a pivot hinge line of one of the half-portions of the IFS 23 and the half-cover 31 a, 31 b corresponding .
• the guiding system of the half-covers 31a, 31b on the pylon 10 combines the translation of the cover 31 and the pivoting of the cover 31 and the IFS 23 during maintenance operations.
• the movements of the half-cowlings 31a, 31b and half-portions of the FS 23 on either side of the pylon 10 are symmetrical with respect to the longitudinal median plane of the nacelle 2 and the pivot movements of the half-covers 31a, 31b and half-portions of the IFS 23 are possible around a single axis, on either side of the pylon 10.
• the fastening and guiding system of the IFS 23 on the pylon 10 is as follows.
• the slides 42 previously described in relation to the guiding system of the half-covers 31a, 31b are coupled to means 25 allowing the pivot connection between each half portion 23a, 23b of the FS 23 and the pylon 10, at 12 o'clock.
• These means 25 may be formed by hooks 25, illustrated in a non-limiting manner to the number of three in Figure 2b, integral with each half-portion 23a, 23b of the IFS 23.
• Each slideway 42 is configured to accommodate one or more of these hooks 25 and prohibit their translation along the corresponding slideway 42.
• each slideway 42 comprises, in an exemplary embodiment, a footprint 47 of shape and dimensions adapted to housing in its concavity, the corresponding hook 25, each hook 25 having a cross section C at its free end.
• each half-portion 23a, 23b of TIFS 23 is pivotally mounted on the pylon 1 0 around the guide rail system 41-slides 42 and locked in translation relative to the latter.
• each half-portion 23a, 23b of the IFS 23 is pivotally mounted on the pylon 10 around the central axes of the slideways 42.
• any device dedicated to the articulation of the IFS 23 and to the fixing of the half portions of the IFS 23 between each other is suppressed.
• locking means 50 for each half-portion 23a, 23b of the IFS 23 in working position may comprise blocking blocks 50 of the IFS 23 next to the hooks 25, in the lower part of the slideways 42, as shown in Figures 6, 7a, 7b.
• These shims 50 are mounted on the tower 10 by suitable means.
• these fixing means are screwing means.
• These shims 50 provide a reinforced support in position of the half-portions 23a, 23b of the IFS 23.
• the deflection grids 32 of the thrust reverser device 30 are retractable at least in part in the median section 6 of the nacelle 2.
• the deflection grids 32 are thus able to slide along an axis parallel to the longitudinal axis A of the nacelle 2 of an upstream position partly within the median section 6 of the nacelle 2 at a downstream position, discovered by the cover 31 during a thrust reversal.
• the means for controlling the sliding of the grids 32 may be independent or not of the means for actuating the sliding of the cover 31 during said inversion to its open position.
• each longitudinal frame 43 on which are mounted the rails 41 of the guide system 40 of each half cover 31 a, 31 b has at least one second slide 48 adapted to cooperate with a rail 32a arranged on an upper end of all the grids.
• the deflection grids 32 are similarly mounted in the upper part of the half-covers 31a, 31b as in the lower part thereof, at six o'clock.
• an aerodynamic fairing panel 36 can be mounted on either side of the suspension pylon 10, by overcoming in the upper part the half-covers 31 a, 31 b.
• Each of these panels 36 is hingedly mounted on the pylon 10 along an axis parallel to the longitudinal axis A, as indicated by the rotation arrow.
• FIGS. 1a to 1c and 15a The actuating means of the movable cowl 31 making it possible to slide from one position to the other of the positions are diagrammatically represented in FIGS. 1a to 1c and 15a.
• these means for actuating the cover 31 comprise two actuators arranged in the upper part of the movable cover, at 12 o'clock, on either side of the suspension pylon 10 and an actuator 61 disposed in the lower part of the cover 31 at 6 o'clock.
• actuators can be of any type, including electric actuators, hydraulic or pneumatic.
• actuators of the linear actuator type with worm and rotating nut there are illustrated actuators of the linear actuator type with worm and rotating nut.
• the actuators at 12 o'clock, in the extension of the associated rails 41.
• the actuator 61 is mounted interposed between the two parts of a connecting island 231, said bifurcation six hours, connecting each half portion 23a, 23b of IFS 23 to the corresponding half-cover 31a, 31b, as will be described in more detail later.
• FIG. 5a to 10b An alternative embodiment of these means for limiting the risk of blocking rails, illustrated in Figures 5a to 10b, is to place each rail 41 in a channel 49 housed in the corresponding slide 42.
• This channel 49 makes it possible to have a better distributed effort on the rail 41 by limiting the peak of effort generated by the substantially horizontal edge due to the cut in the slideway 42 allowing the rotational movement of the rail 41.
• These means thus comprise, on either side of the pylon 10, a gutter 49 configured to be housed in the guiding system of the cover 31.
• Each of these gutters 49 is in the form of a tube, pierced with a notch 491 longitudinal for the passage of the corresponding rail 41, this tube extending obviously along the pylon 10 suspension.
• the central axis of the be corresponds to the central axis of the corresponding rail 41.
• Each guide rail 41 is movable in translation along the gutters 49, the latter being locked in translation relative to the corresponding slides 42.
• a shoulder 492 adapted to cooperate with an abutment formed on the corresponding slideway 42 is provided, this stop preventing any translation of the gutter 49.
• a second stop 493 is provided in the form of an oblong profile attached to the corresponding end of the slideway 42.
• this abutment 493 further comprises a shape and complementary dimensions of the extended rail 42 of the retaining rod 44 to the longitudinal frame 43 associated with the trough 49.
• each channel 49 is rotatable about the longitudinal axis of the slide 42 corresponding.
• Each gutter 49 thus accompanies the rotational movements of the associated rail 42 causing the movement of the cover 31 between the different working and maintenance positions.
• a lower guide system connects each half-portion 23a, 23b of the IFS 23 and the corresponding half-cover 31a, 31b.
• each half-cover 31a, 31b has a free edge 34, opposite to the upper edge 33, on which is mounted a guide section 70 configured to have a double guide slide 71, 72 having, each , a central axis parallel to the longitudinal axis A of the nacelle.
• Each profile 70 extending longitudinally on an upstream part of the half-cover 31a, 31b and not over its entire length.
• One of the slides 72 is provided to ensure the translational movement of the grids 32 in cooperation with a guide rail mounted on the latter, as indicated above with respect to the upper part of the cover 31.
• the second slide 71 is adapted to cooperate with a guide rail 80 mounted on the corresponding half-portion 23a, 23b of the IFS 23.
• each guide rail 80 is mounted on the corresponding half-fork portion 231, vertically extending the lower end of each half-portion 23a, 23b of NFS 23 and integral with NFS. 23.
• Such a mounting of the cover 31 and the IFS 23 makes it possible, on either side of the pylon 10, a unitary assembly of half-shell type, formed by a half cover 31 a, 31 b, the grid system 32 and associated half-portion 23a, 23b IFS 23, this assembly being rotatable about a single axis defined by the cover guiding system 31 in the upper part of the hood, as shown in Figures 14b and 14b.
• downstream portion of the turbojet engine 3 can be accessed through the lateral opening, outwardly, of said unitary unit concerned, on either side of the pylon 10.
• the actuator 61 for controlling the displacement of the cover 31 is placed in the concavity of the bifurcation 231 formed when the two half-parts 23a, 23b of the IFS are joined together. so that it is not an obstacle to the opening kinematics of the cover 31.
• this actuator 61 helps to limit the risks of blocking the cover 31 during an inverted jet phase in particular.
• This actuator 61 is carried by only one of the two half-parts 23a, 23b of NFS 23 and the half-cover 31a, 31b corresponding.
• the actuator 61 is a linear actuator worm and rotating nut.
• Such an actuator 61 comprises a rotary nut 61 1 rotatably mounted about the longitudinal axis A of the nacelle 2 and driven by an electric motor 612 mounted on one of the branches of the bifurcation 231 on the right half or left half of NFS 23.
• the actuator 61 further comprises a translating worm gear 613 provided with a threaded portion, in order to be suitably coupled with the rotary nut 61 1.
• This screw 613 extends along the longitudinal axis A of the nacelle, fixed to one of the guide profiles 70, via a connecting element 73 in which it is housed via a support fixed at its free end.
• This endless screw 613 mates with the second guide profile 70 via a second connecting section similar to the first, provided with a slot in which the support of the screw 61 3 is also housed at the closure. in rotation of the half-covers 31a, 31b between them.
• each rail 80 with respect to its associated slideway 71 and, consequently, of the cover 31 is ensured by the endless screw 613, the translation of which is itself carried out by the rotary nut 61 in engagement with the pitch of this screw 613, and driven by the motor 612.
• Such an actuator 61 ensures the displacement in translation of each half cowl 31 a, 31 b upstream and downstream of the nacelle 2 between its open and closed positions, thanks to the rotation of the driven nut 61 1. by the motor 612, said nut 61 1 being fixed in translation relative to NFS 23.
• the mounting of the guide system and the actuator 61 avoids the need to uncouple the actuator with the guidance system during maintenance operations.
• the junction of the two half-covers 31a, 31b is, in part, off-axis with respect to the 6H axis.
• locking means 90 of the half-covers 31a, 31b mounted in the lower part of the half-covers 31a, 31b can be provided to keep closed the half-covers 31a, 31b in the lower part, without disturbing the kinematics of opening / closing of these.
• These locking means 90 can be of any type.
• they comprise a series of hooks on one of the half-covers 31a, 31b, adapted to cooperate with retaining means mounted on the other of the half-covers 31 a, 31 b, thus ensuring the locking of the cover 31 in the lower part.
• the locking means 90 are grouped in the upstream part of the half-covers 31a, 31b to release the downstream parts thereof.
• the bifurcation 61 1 ensuring the junction between the cover 31 and the IFS 23 in the lower part has a trailing edge thinner than its leading edge.
• this bifurcation is also reduced longitudinally of the order of 60% compared to the bifurcations of the prior art devices.
• the mode of operation of a nacelle rear assembly according to the invention is as follows.
• the half-covers 31a, 31b of which only a longitudinal frame 43 is shown, locked together at the bottom, move downstream of the nacelle (as indicated by FIG. the arrow in Figure 9b or the cover 31 is in the closed position) to discover the deflection grids 32 and rotate, if necessary, the shutters to close the vein 7 of cold air flow.
• each guide rail 41 slides in the slideway
• gutters 49 are locked in translation during operation of the nacelle and, in particular in thrust reversal phase.
• each half-cover 31 a, 31 b is moved in translation, downstream of the nacelle, in the direction of its opening position of the cover 31 corresponding to a thrust reversal phase described above but without reaching this position.
• the cover 31 is in an intermediate position between its closed and open position, a position adapted to disengage the cover 31 from the deflection edge of the fan casing.
• the one or more half-shells are pivoted towards the outside of the turbojet engine, namely, the assembly concerned of half-cowl 31a -difference grids 32 -demi part 23a, 23b IFS 23, integral in rotation about the sliding axis of the corresponding half-cover 31.
• the gutters 49 also pivot about the axis of sliding of the corresponding half-cover 31 as well as the hooks 25 of the half portion of the IFS 23.
• turbojet engine is released as follows, some stages of which are illustrated in FIGS. 15a to 15e.
• the half-cover 31 a, 31 b concerned simultaneously with the deflection grids it carries, is deposited from the suspension pylon 10, releasing, in particular, the rails 41 of the cover 31 of the slideways 42 of the pylon 10 , by translating them downstream of the nacelle 2 ( Figure 15b).
• the IFS 23 blocking wedges are disassembled after pivoting the IFS 23 half-portions 23a, 23b into the maintenance position.
• the channel 49 of the corresponding slideway 41 is deposited laterally (passage of FIGS. 15d to 15e).

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• Aviation & Aerospace Engineering (AREA)
• Wind Motors (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

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• 2011
  • 2011-09-16 FR FR1158247A patent/FR2980173B1/fr active Active
• 2012
  • 2012-09-07 CA CA2845031A patent/CA2845031A1/fr not_active Abandoned
  • 2012-09-07 CN CN201280045053.4A patent/CN103796919A/zh active Pending
  • 2012-09-07 EP EP12767045.3A patent/EP2766259A1/de not_active Withdrawn
  • 2012-09-07 BR BR112014004264A patent/BR112014004264A2/pt not_active IP Right Cessation
  • 2012-09-07 RU RU2014113662/11A patent/RU2014113662A/ru not_active Application Discontinuation
  • 2012-09-07 WO PCT/FR2012/052005 patent/WO2013038093A1/fr active Application Filing
• 2014
  • 2014-03-07 US US14/200,365 patent/US10036323B2/en active Active

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