• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a system (58) for the installation and removal of a propulsion unit (10) on a mast (11) of an aircraft, a propulsion unit (10) of the type comprising a nacelle (12) and a turbojet engine. , the turbojet engine being connected to the mast (11) via at least one front suspension (24) and a rear suspension (26), characterized in that it comprises a carrier structure (34) which is adapted to carry a thrust reverser device, a front suspension (24) of the turbojet, which carries a front part of the carrier structure (34), and which is removably attached to a front part of the mast (11). ), and a rear suspension (26) of the turbojet, which carries a rear part of the carrier structure (34), and which is removably attached to a rear part of the mast (11), and the separation of said suspensions (24, 26) of the mast (11) for removing the propulsion assembly (10) mounted on the mast (11).
    公开号:FR3031726A1
    申请号:FR1550490
    申请日:2015-01-21
    公开日:2016-07-22
    发明作者:Patrick Boileau；Olivier Kerbler；Julien Lezerac；Loic Grall；Aurelien Gonzalez；Ludovic Toupet
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to a system for the installation and removal of a propulsion unit on a mast of an aircraft, the system comprising a thrust reverser device. An aircraft is generally driven by several turbojet engines each housed in a nacelle housing a set of ancillary actuators related to its operation and providing various functions when the turbojet engine is in operation or stopped. These ancillary actuating devices comprise in particular a thrust reversal device. A turbojet engine nacelle generally has a substantially tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of said turbojet engine, a downstream section intended to surround the combustion chamber of the turbojet engine and possibly including means thrust reverser, 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 through the blades of the rotating fan a flow of hot air (primary flow) and a cold air flow (secondary flow) 20 which circulates at the outside of the turbojet engine through an annular passage, also called a vein, formed between 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 role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the air ejected from the turbojet engine. In this phase, the inverter obstructs at least part of the cold flow vein and directs this flow towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels and air brakes of the plane. In general, the structure of an inverter comprises a hood which is mounted movable in longitudinal translation from front to rear in a direction substantially parallel to the axis of the nacelle, between a closed position in which the hood provides the aerodynamic continuity of the nacelle, and an open position in which the hood opens a passage 35 in the nacelle In the case of an inverter with deflection grids, the reorientation of the air flow is performed by deflection grids, associated with inversion flaps at least partially block the air flow duct, the hood having a simple sliding function to discover or cover these deflection grids. The inversion flaps, also called locking flaps, for their part, are activated and driven by the sliding of the movable cowl to come at least partially block the vein downstream of the grids, so as to optimize the reorientation of the flow of 'cold air.
    [0002] O-structure nacelles, known in the English terminology "O-Duct", are known which have a downstream structure having a single substantially peripheral structure extending from one side of the reactor mast to the other side. . It follows that such a structure generally has a single substantially peripheral hood which, for maintenance purposes, opens by downstream translation along the longitudinal axis of the nacelle. For a detailed description, reference may be made to documents FR 2 911 372 and FR 2 952 681. In addition, the 0-structure boats include deflection grids which are mounted to be movable in translation and able to be retracted at least partially. in the thickness of the central section of the nacelle and thus overlap the fan casing when the thrust reverser is inactive, in the direct jet position. In the reverse thrust position, the deflection grids are displaced with the movable cowl. In the case of a thrust reverser for a nacelle structure 0, the mast can be equipped with rails for sliding of the movable cowl and grids. On modern, large propellant assemblies with highly flexible structures, this configuration can induce significant stresses in the thrust reverser structure. Also known thrust reversal device described in FR-A-3002785, which comprises rails which are arranged on either side of the mast and which ensure the sliding of the movable cowl and deflection grids. This type of device has drawbacks in particular in that in case of relative displacement of the turbojet engine with respect to the mast, the movable gates, which are fixed on the mast, risks being subjected to deformation forces. Indeed, to limit the volume of modern nacelles, the mobile grids section is limited to limit their size, so that the inertia of the grids and the mechanical strength they oppose is reduced. In addition, there is also a risk of relative movement of the rails between them and significant geometric variations that may compromise the proper functioning of the kinematics of the thrust reverser. Finally, the assembly / disassembly of the propulsion unit involves dismantling all or part of the thrust reverser. The present invention aims in particular to solve these disadvantages and relates for this purpose to a system for the installation and removal of a propulsion assembly on a mast of an aircraft, a propulsion assembly 15 of the type comprising a nacelle and a turbojet, the nacelle extending longitudinally from front to rear along a longitudinal axis, the turbojet engine being connected to the mast via at least one of a front suspension and a rear suspension, characterized in that it comprises: A carrier structure which is adapted to carry a thrust reverser device and which extends longitudinally; a front suspension of the turbojet engine, which carries a front part of the carrier structure, and which is removably fixed on a the front part of the mast, and 25 - a rear suspension of the turbojet engine, which carries a rear part of the supporting structure, and which is removably attached to a rear part of the mast, the lidarization said mast suspensions for removing the propulsion assembly mounted on the mast. Thus, the system according to the invention makes it possible to reduce the time required for the installation and removal of the propulsion unit, which is detachable from the mast by releasing the front and rear plates from the mast. According to another characteristic, the thrust reverser device comprises at least: a cover which is mounted movable in longitudinal translation from before backwards in a direction substantially parallel to the axis of the nacelle, between a closed position wherein the hood provides aerodynamic continuity of the nacelle, and an open position in which the hood opens a passage in the nacelle, and - at least one sliding gate of reverse thrust which is driven by the movable cowl, between a retracted position, corresponding to the closed position of the cover, and a thrust reversing position corresponding to the opening position of the cover, in which position the sliding gate is moved downstream so as to be able to extend through said passage opened by the hood, and in that the support structure has the shape of a cradle which comprises a first spar and a second spar that extends longitudinally on both sides of the mast, said longitudinal members each carrying sliding guide means of the movable cowl and the sliding grid. This feature allows the thrust reverser device 15 to follow the motions of the engine. In addition, the sliding guide means of the movable cowl and the sliding gate comprise at least a first pair of guide rails of the gate, comprising a first rail and a second rail which are arranged on either side of the mast. and which are adapted to slide the thrust reversing gate, and the sliding guide means of the movable cowl and the sliding gate comprise at least a second pair of hood guide rails, comprising a first rail and a second rail which are arranged on either side of the mast and which are designed to ensure the sliding of the movable cowl. In addition, the first rail of the first pair of guide rails of the gate and the first rail of the second pair of guide rails of the cover are aligned on the same straight line, and the second rail of the first pair of rails. guiding the gate and the second rail of the second pair of guide rails of the cover are aligned on the same straight line. Also, the first spar of the carrying structure comprises: a first connecting portion which is delimited laterally by a first longitudinal edge which extends in the vicinity of the mast, and by a second longitudinal edge which carries the first guide rail of the grid, a second connecting portion which is delimited laterally by a first longitudinal edge which extends in the vicinity of the mast, and by a second longitudinal edge which carries the second guide rail of the grid.
    [0003] Advantageously, each connecting portion comprises an opening which is uncovered by the movable cowl in its open position, to allow redirection of the air flow, said opening being adapted to be completely or partially obstructed as required.
    [0004] The supporting structure has a symmetrical design along a plane of symmetry passing through the axis of the nacelle. In addition, the front suspension of the turbojet engine is connected to a fan casing of the turbojet engine. Also, to avoid spacing the spars, the system according to the invention is equipped with a removable retaining means of the carrier structure, which connects the first spar and the second spar of the carrier structure on a first side and on a second side respectively of the mast. According to an alternative embodiment, the thrust reverser device comprises islands of a fixed internal structure of the inverter which are connected to the carrier structure. According to another embodiment, the system comprises at least one security lock of inadvertent non-deployment of the movable cover. The invention also relates to a turbojet engine nacelle which is equipped with at least one system for the installation and removal of a propulsion assembly of the type described above. Other characteristics and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended drawings in which: FIG. 1 is a diagrammatic overall view of the assembly which illustrates a nacelle equipped with a thrust reverser device comprising a bearing structure carrying a cap shown in the closed position, according to the invention; - Figure 2 is a schematic top view similar to that of Figure 1, which illustrates the movable cover in the open position; FIG. 3 is a detail view in perspective, which illustrates the connected support structure on the front and rear suspensions of the turbojet engine; - Figure 4 is a perspective detail view, which illustrates the connection of the carrier structure on the front suspension; Figure 5 is a detail perspective view illustrating the connection of the carrier structure to the rear suspension; FIG. 6 is a detailed perspective view which illustrates the carrier structure alone; - Figure 7 is a detailed perspective view illustrating the front and rear suspensions of the turbojet engine.
    [0005] In the description and the claims, the terms "upper", "lower" and "low", "high" will be used in a nonlimiting manner with reference to the upper part and the lower part respectively of FIGS. 1 to 8. to clarify the description and the claims, the longitudinal, vertical and transverse terminology will be adopted in a nonlimiting manner with reference to the trihedron L, V, T indicated in the figures, whose longitudinal axis L is parallel to the axis of the nacelle. Note also that in the present patent application, the terms "upstream" and "downstream" must be understood in relation to the flow of air flow inside the propulsion unit formed by the nacelle and the turbojet, that is to say from left to right according to Figures 1 to 8. Also, to facilitate understanding of the description, identical and symmetrical elements in the plane P of symmetry are indicated by the same reference numerals distinguished by the letter "a" or "b". FIG. 1 shows a propulsion unit 10 mounted on a mast 11 of an aircraft, the propulsion unit 10 comprising a nacelle 12 of the 0 structure type, and a turbojet engine (not visible) housed in the nacelle 12. The nacelle 12 extends longitudinally from front to rear along a longitudinal axis A. Here, by turbojet, is meant the part also called "engine" of the propulsion unit 10. The nacelle 12 has a substantially tubular structure which extends longitudinally along the central axis A and which comprises an air inlet 14 upstream of the turbojet engine, a median section 16 intended to surround a fan 18 of the turbojet engine, a downstream section 20 intended to surround the combustion chamber of the turbojet engine and incorporating a device 21 for inverting thrust by redirecting an air flow circulating from upstream to downstream in a vein of the nacelle 12, and an exhaust nozzle 22 whose output is located downstream of the turbojet engine.
    [0006] As can be seen in FIG. 4, the turbojet engine is connected to the mast 11 via a front suspension 24 fastened to the fan casing 18 of the turbojet engine, and to a rear suspension 26. thrust reversal comprises a cover 28 which is mounted movable in longitudinal translation back and forth along the axis A of the nacelle 12, between a closed position, shown in Figure 1, in which the cover 28 ensures continuity aerodynamic of the nacelle 12, and an open position, shown in Figure 2, wherein the cover 28 opens a passage 30 of deflection of the air flow in the nacelle 12.
    [0007] In addition, the device 21 comprises sliding sliding gates 32, which are driven by the movable cover 28, between a position retracted between the fan casing 18 and the outer casing (not shown in FIGS. 1 and 2). of the nacelle 12, corresponding to the closed position of the cover 28, and a thrust reversing position corresponding to the open position of the cover 28, position in which the sliding gates 32 are moved downstream so as to it can extend through the passage 30 open by the cover 28 movable in the nacelle 12. In accordance with the invention, the thrust reverser device 21 is equipped with a carrier structure 34 forming a cradle, shown in more detail. to Figures 3 to 6, which belongs to a system 58 for the installation and removal of the propulsion system 10 on the mast 11. The carrier structure 34 has a symmetrical design along a plane P symmetrical vertical ie passing through the longitudinal axis A of the nacelle 12. With reference to FIG. 3, the carrier structure 34 comprises a first sill 36a and a second sill 36b which extend longitudinally on either side of the mast 11. The longitudinal members 36a, 36b each comprise sliding guide means for the movable cover 28 and sliding gates 32. The sliding guiding means comprises a first pair of grid guide rails 32 which comprises a longitudinally extending first longitudinally extending first rail 40a and a second rail 40b, which are arranged symmetrically along the plane P of symmetry, and which are designed to ensure the sliding of the grids 32 of thrust reversal. For this purpose, with reference to FIG. 2, the grids 32, of generally C-shaped shape around the axis A of the nacelle 12, have a first guide edge 42a and a second guide edge 42b which cooperate with the first rail 40a and the second rail 40b respectively. In addition, the sliding guide means comprise a second pair of guide rails of the cover 28 which comprises a first rail 44a and a second rail 44b which extend longitudinally along the mast 11, which are arranged symmetrically along the plane P of symmetry, and which are designed to ensure the sliding of the hood 28 mobile. For this purpose, the cover 28 movable, generally C-shaped around the axis A of the nacelle 12, has a first guide edge 46a 10 and a second guide edge 46b which cooperate with the first rail 44a and the second rail 44b respectively. The guide rails of the grids 32 are spaced transversely relative to the guide rails of the cover 28 to allow the arrangement of the front suspension 24 between the guide rails of the grids 32. In addition, the guide rails of the grids 32 can be offset vertically also relative to the guide rails of the cover 28. However, when such an arrangement is not necessary, according to an alternative embodiment not shown, the first rail 40a of the first pair of guide rails of the grids 32 and the first rail 44a of the second pair of hood guide rails 28 are aligned on the same straight line. Similarly, by symmetry, the second rail 40b of the first pair of grid guide rails 32 and the second rail 44b of the second pair of hood guide rails 28 are aligned on the same straight line. Thus, according to this embodiment, the guide rails of the grids 32 and the guide rails of the cover 28 can be made in one piece. With reference to FIG. 6, the first spar 36a of the cradle 34 has a first connecting portion 48a which is delimited laterally by a first longitudinal edge 50a which extends in the vicinity of the mast 11, and by a second longitudinal edge 52a which carries the first rail 40a for guiding the sliding gates 32. By symmetry, the second spar 36b of the cradle 34 comprises a second connecting portion 48b which is delimited laterally by a first longitudinal edge 50b which extends in the vicinity of the mast 11, and by a second longitudinal edge 52b which carries the second rail 40b guide sliding grids 32.
    [0008] Also, each connecting portion 48a, 48b comprises an opening 54a, 54b which is exposed by the cover 28 movable in its open position, to allow the redirection of the air flow. According to a preferred exemplary embodiment, illustrated in FIG. 6, each opening 54a, 54b is equipped with a fixed gate 56a, 56b fixed respectively, each gate comprising fins designed to redirect the flow of air towards the front of the gate. nacelle 12, to participate in the reverse thrust, when the movable cover 28 is in its open position. Advantageously, the fins of the fixed gates 56a, 56b may be arranged so as to orient the flow of air at an angle inclined transversely to avoid redirecting the flow of air to the wing of the aircraft. Alternatively, each opening 54a, 54b, or one of the openings 54a, 54b may be partially or completely obstructed to optimize the effectiveness of the thrust reverser. Indeed, by playing on the ejection surface of the openings 54a, 54b, it is possible to play on the ratio between the nozzle ejection surface of the propulsion unit and the ejection surface of the passage 30 discovered. by the movable cover 28 of the inverter. This ratio, which ideally tends to value one, is known as "area match". According to the invention, the system 58 for the installation and removal of the propulsion unit 10 comprises the carrier structure 34 which is adapted to carry the sliding gates 32 and the movable cover 28. The system 58 is designed to favor the installation and removal of the propulsion unit 10 by releasing the front suspension 24 and the rear suspension 26 which connect the turbojet engine to the mast 11. For this purpose, the support structure 34 comprises a part before which is connected to the front suspension 24 of the turbojet, and a rear portion which is connected to the rear suspension 26 of the turbojet engine. As can be seen in FIGS. 3 to 7, the carrying structure 34 comprises a first tab 62a which extends horizontally from the inner edge 50a of the first spar 36a of the cradle 34. By symmetry along the plane P, the bearing structure 34 comprises a second tab 62b which horizontally from the inner edge 50b of the second spar 36b of the cradle 34. In a complementary manner, the front suspension 24 of the turbojet engine has a first flat portion 66a designed to be in vertical abutment and fixed on the associated first tab 62a the supporting structure 34 by means of two bolts 68a, a second flat 66b designed to be in vertical abutment and fixed on the second associated lug 62b of the supporting structure 34 by means of two bolts 68b, and a third central flat portion 70 interposed between two other flats. Central flat 70 is in vertical support on a bracket 72 which extends horizontally from the free end of the mast 11 and which delimits a rib 74 of reinforcement. The rib 74 defines a through hole 76 adapted to cooperate with a centering pin 78 mounted on the front suspension 24. In addition, the bracket 72 is removably attached to the front suspension 24 by four bolts 80. Also, first spar 36a of the cradle 34 comprises a first branch 84a which extends generally longitudinally rearwardly 15 to form a first yoke 86a of connection. The first yoke 86a has two lugs which delimit between them a vertical slot 88a designed to cooperate with a first link 90a. The first link 90a is connected at one end to the first clevis 86a by a first axis 92a, and at another end to the rear suspension 26 of the turbojet engine by two axes 94a whose eccentric axis allows a transverse play adjustment of mounting between the cradle 34 and the mast 11. According to FIG. 7, the rear suspension 26 is delimited vertically by a lower face 96 arranged facing the turbocompressor, and an upper face 98 which bears on a lower face of the mast 11. moreover, the mast 11 comprises a first bracket 100a which extends from a first side 102a of the mast and which has a bearing surface 104a in vertical support on the upper face 98 of the rear suspension 26. The first bracket 100a is removably attached to the rear suspension 26 by two bolts 106a. By symmetry along the plane P, the second spar 36b of the cradle 34 comprises a second branch 84b which extends generally longitudinally rearwardly to form a second yoke 86b of connection.
    [0009] The second yoke 86b has two lugs which delimit between them a slot 88b vertical designed to cooperate with a second link 90b. The second link 90b is connected at one end to the second clevis 86b by a first axis 92b, and at another end to the rear suspension 26 by two axes (not visible) whose eccentric axis allows adjustment of the mounting set of the cradle. 34. In addition, the mast 11 comprises a second bracket (not visible) which extends from a second side 102b of the mast and which has a bearing surface 10 in vertical support on the upper face 98 of the rear suspension 26. The second bracket is removably attached to the rear suspension 26 by two bolts. Also, the lower face of the mast 11 defines a through hole which cooperates with a centering pin 110 which extends vertically from the rear suspension 26. Thus, the invention allows a quick and easy installation and removal of the propulsion unit on the mast 11 by dismounting the mast 11 front suspension 24 and the rear suspension 26. This feature in particular reduces the time required 20 airlines to change the propulsion system on an aircraft. In addition, the invention allows a reduction in the time required to prepare the assembly of the nacelle and turbojet prior to mounting on aircraft. Also, the invention allows the thrust reverser device to follow globally the movements of the turbojet engine, the bearing structure 34 being connected indirectly to the fan casing 18. This feature allows in particular the sliding grids 32 and the movable cover 28, as well as their guide rails 40a, 40b, 44a, 44b to follow the movement of the turbocharger. According to an exemplary embodiment of the invention illustrated in Figure 4, the system 58 is equipped with a removable retaining means of the carrier structure 34, or abutment means, which connects the first spar 36a and the second spar 36b of the carrier structure 34 on the first flank 102a and on the second flank 102b respectively of the mast 11, in order to prevent reciprocal transverse spacing of the longitudinal members 36a, 36b of the carrier structure 34.
    [0010] However, the removable retaining means is designed to allow longitudinal movement and vertical movement of the carrier structure 34 with respect to the mast 11. For this purpose, the retaining means comprises a first longitudinal profile 112a of U-shaped section, which delimits a longitudinal groove 114a open downwards, facing the turbojet, and which is fixed on the first sidewall 102a of the mast 11. Complementarily, the retaining means comprises a first retaining tab 116a which extends vertically upwardly from the first spar 36a of the carrier structure 34, and which extends longitudinally in the groove 114a of the first profile 112a provided for this purpose. The first tab 116a and the first associated section are fixed together by three transverse retaining pins 118a which are removably mounted to enable the carrier structure 34 to be released from the mast 11. By symmetry along the plane P of symmetry, the means of retaining comprises a second longitudinal profile 112b, of U-shaped section, which delimits a longitudinal groove open downwards, facing the turbojet, and which is fixed on the second sidewall 102b of the mast 11. Complementarily, the retaining means comprises a second 20 retaining tab which extends vertically upwards from the first spar 36a of the carrier structure 34, and which extends longitudinally in the groove of the second section 112b provided for this purpose. The second leg and the associated second section 112b are fastened together by three transverse retaining axes which are removably mounted to enable the carrier structure 34 to be released from the mast 11. Advantageously, the retaining means thus designed does not interfere with the installation and removal in a vertical movement of the propulsion unit on the mast 11. However, by way of non-limiting embodiment, according to a variant embodiment not shown, the retaining means may include sleepers, or connecting rods, which extend transversely under the mast 11 and which interconnect the two longitudinal members 36a, 36b of the support structure 34. Advantageously, according to a variant embodiment not shown, the thrust reverser comprises islands of a fixed internal structure 35 which are connected to the supporting structure 34.
    [0011] Similarly, according to an alternative embodiment not shown, the system according to the invention comprises safety latches designed to prevent inadvertent deployment of the cover 28 mobile. The present description of the invention is given by way of nonlimiting example.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. System (58) for the installation and removal of a propulsion unit (10) on a mast (11) of an aircraft, a propulsion unit (10) of the type comprising a nacelle (12) and a turbojet, the nacelle (12) ) extending longitudinally from front to back along a longitudinal axis (A), the turbojet being connected to the mast (11) via at least one front suspension (24) and a rear suspension (26), characterized in that it comprises: - a carrier structure (34) which is adapted to carry a device (21) thrust reverser and which extends longitudinally - a front suspension (24) of the turbojet engine , which carries a front part of the carrier structure (34), and which is removably attached to a front part of the mast (11), and - a rear suspension (26) of the turbojet, which carries a rear part of the structure carrier (34), and which is removably attached to a rear portion of the mast (11), and the separation of said suspension (24, 26) of the mast (11) for removing the propulsion assembly (10) mounted on the mast (11).
    [0002]
    2. System (58) for the installation and removal of a propulsion unit (10) according to claim 1, characterized in that the device (21) for reversing thrust comprises at least: - a cover (28) which is mounted movable in longitudinal translation from front to rear in a direction substantially parallel to the axis (A) of the nacelle (12), between a closed position in which the hood (28) ensures the aerodynamic continuity of the nacelle ( 12), and an open position in which the hood (28) opens a passage (30) in the nacelle (12), and - at least one sliding gate (32) of thrust reversal which is driven by the hood (28) movable between a retracted position, corresponding to the closed position of the cover (28), and a thrust reversing position corresponding to the open position of the cover (28), position in which the grid (32) ) is moved downstream so as to extend through said passage ( 30) open by the hood (28), and in that the carrier structure (34) has the shape of a cradle which comprises a first spar (36a) and a second spar (36b) which extend longitudinally from and other of the mast (11), said longitudinal members (36a, 36b) each carrying sliding guide means of the cover (28) movable and the gate (32) sliding.
    [0003]
    3. System (58) for the installation and removal of a propulsion unit 5 (10) according to claim 2, characterized in that the sliding guide means of the cover (28) movable and the gate (32) sliding comprise at least a first pair of guide rails (40a, 40b) for guiding the gate (32), comprising a first rail (40a) and a second rail (40b) which are arranged on either side of the mast (11) and which are adapted to slide the thrust reversing gate (32), and that the sliding guide means of the movable hood (28) and the sliding gate (32) comprise at least one second a pair of cover guiding rails (44a, 44b), comprising a first rail (44a) and a second rail (44b) which are arranged on either side of the mast (11) and which are designed to ensure sliding of the hood (28) movable.
    [0004]
    4. System (58) for the installation and removal of a propulsion unit (10) according to claim 3, characterized in that the first rail (40a) of the first pair of rails (40a, 40b) for guiding the gate (32) and the first rail (44a) of the second pair of hood guiding rails (44a, 44b) are aligned on one straight line, and the second rail (40b) of the first pair of gate guiding rails (40a, 40b) (32) and the second rail (44b) of the second pair of hood guiding rails (44a, 44b) are aligned on the same straight line.
    [0005]
    5. System (58) for the installation and removal of a propulsion unit (10) according to any one of claims 2 to 4, characterized in that the first spar (36a) of the carrier structure (34) comprises a first connecting portion (48a) which is delimited laterally by a first longitudinal edge (50a) extending in the vicinity of the mast (11), and by a second longitudinal edge (52a) carrying the first rail (40a). ) For guiding the grid (32), - a second connecting portion (48b) which is delimited laterally by a first longitudinal edge (50b) extending in the vicinity of the mast (11), and by a second edge ( 52b) which carries the second guide rail (40b) of the gate (32). 35
    [0006]
    6. System (58) for the installation and removal of a propulsion unit (10) according to claim 5, characterized in that each connecting portion (48a, 48b) comprises an opening (54a) which is uncovered by the hood (28) movable in its open position, to allow the redirection of the air flow, said opening (54a) being adapted to be fully or partially obstructed as required.
    [0007]
    7. System (58) for the installation and removal of a propulsion unit (10) according to any one of the preceding claims, characterized in that the carrier structure (34) has a symmetrical design along a plane (P) of symmetry passing through the axis (A) of the nacelle (12).
    [0008]
    8. System (58) for the installation and removal of a propulsion unit 10 (10) according to any one of the preceding claims, characterized in that the front suspension (24) of the turbojet engine is connected to a fan casing ( 18) of the turbojet engine.
    [0009]
    9. System (58) for the installation and removal of a propulsion unit (10) according to any one of claims 2 to 8, characterized in that it is equipped with a removable retaining means of the structure carrier (34), which connects the first spar (36a) and the second spar (36b) of the carrier structure (34) on a first flank and a second flank respectively of the mast (11) to ensure the passage of forces between the spars (36a, 36b).
    [0010]
    10. System (58) for the installation and removal of a propulsion unit 20 (10) according to any one of the preceding claims, characterized in that the thrust reverser device comprises islands of a fixed internal structure of the inverter which are connected to the carrier structure (34).
    [0011]
    11. System (58) for the installation and removal of a propulsion unit (10) according to any one of claims 2 to 9, characterized in that it comprises at least one safety lock of inadvertent non-deployment of hood (28) movable.
    [0012]
    12. Nacelle (12) turbojet engine, characterized in that it is equipped with at least one system (58) for the installation and removal of a propulsion unit (10) according to any one of the preceding claims. 30
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    同族专利:
    公开号 | 公开日
    US20170313432A1|2017-11-02|
    WO2016116710A1|2016-07-28|
    EP3247635B1|2018-05-16|
    US11186379B2|2021-11-30|
    FR3031726B1|2017-02-24|
    EP3247635A1|2017-11-29|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2102187A1|1970-08-11|1972-04-07|Secretaire Etat Royaume|
    CN103112595A|2013-02-06|2013-05-22|中国商用飞机有限责任公司|Integral suspended structure of propelling system|
    WO2014132011A1|2013-03-01|2014-09-04|Aircelle|Thrust reverser device|FR3073572A1|2017-11-16|2019-05-17|Safran Nacelles|MOVING GRID PUSH INVERTER FOR AN AIRCRAFT PROPULSION ASSEMBLY AND METHODS OF MOUNTING AND DISASSEMBLING THEREFOR|
    FR3087497A1|2018-10-23|2020-04-24|Safran Nacelles|HIGH AXIAL RETENTION FOR A D-STRUCTURE SLIDING GRILLE INVERTER|US4458863A|1980-03-10|1984-07-10|The Boeing Company|Strut supported inlet|
    FR2496766B1|1980-12-23|1983-02-04|Snecma|
    FR2911372B1|2007-01-15|2009-02-27|Aircelle Sa|TRANSLATABLE PUSH INVERTER FOR REACTION ENGINE|
    FR2922958B1|2007-10-25|2009-11-20|Aircelle Sa|THRUST INVERTER WITH GRILLS|
    FR2952681B1|2009-11-18|2017-10-06|Aircelle Sa|PUSH INVERTER|
    FR2974150B1|2011-04-14|2013-04-12|Aircelle Sa|THRUST INVERTER FOR AIRCRAFT TURBOREACTOR|
    FR2995637B1|2012-09-19|2018-05-11|Safran Nacelles|FIXED STRUCTURE OF PUSH REVERSING DEVICE|
    FR3031726B1|2015-01-21|2017-02-24|Aircelle Sa|SYSTEM FOR THE INSTALLATION AND REMOVAL OF A PROPULSIVE ASSEMBLY ON A MAT OF AN AIRCRAFT|
    FR3031725B1|2015-01-21|2018-06-01|Safran Nacelles|AIRCRAFT TURBO BOILER NACELLE|FR3031726B1|2015-01-21|2017-02-24|Aircelle Sa|SYSTEM FOR THE INSTALLATION AND REMOVAL OF A PROPULSIVE ASSEMBLY ON A MAT OF AN AIRCRAFT|
    FR3065442B1|2017-04-25|2021-03-19|Airbus Operations Sas|ENGINE ASSEMBLY FOR AIRCRAFT INCLUDING A FRONT ENGINE ATTACHMENT INTEGRATED IN THE HOUSING OF THE MAST|
    法律状态:
    2015-12-30| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-22| PLSC| Publication of the preliminary search report|Effective date: 20160722 |
    2017-01-05| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-19| PLFP| Fee payment|Year of fee payment: 4 |
    2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |
    2019-09-27| ST| Notification of lapse|Effective date: 20190906 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550490A|FR3031726B1|2015-01-21|2015-01-21|SYSTEM FOR THE INSTALLATION AND REMOVAL OF A PROPULSIVE ASSEMBLY ON A MAT OF AN AIRCRAFT|FR1550490A| FR3031726B1|2015-01-21|2015-01-21|SYSTEM FOR THE INSTALLATION AND REMOVAL OF A PROPULSIVE ASSEMBLY ON A MAT OF AN AIRCRAFT|
    EP16702757.2A| EP3247635B1|2015-01-21|2016-01-21|System for mounting a propulsion assembly onto a pylon of an aircraft and dismounting same therefrom|
    PCT/FR2016/050120| WO2016116710A1|2015-01-21|2016-01-21|System for mounting a propulsion assembly onto a pylon of an aircraft and dismounting same therefrom|
    US15/653,971| US11186379B2|2015-01-21|2017-07-19|System for installing and removing a propulsion unit on a pylon of an aircraft|
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