• 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 turbojet comprising a motor, a fan casing and a nacelle (102) comprising a fixed structure (206) and an inverter system having a moving assembly (207) with a movable cover (207a) and a frame (207b). ), wherein the movable assembly (207) is movable in translation on the fixed structure (206) between an advanced position and a retracted position to define a window between the secondary vein (208) and the outside of the nacelle (102) , inner (104) and outer (105) doors, a slider (214) movable in translation between a first position and a second position, wherein each door is hinged by a rear edge on the slider (214) between a stored position and an extended position, an actuator for translational movement of the slider (214) from the first position to the second position and an actuator for moving the frame (207b) from the advanced position to the position remote ion.
    公开号:FR3078111A1
    申请号:FR1851556
    申请日:2018-02-22
    公开日:2019-08-23
    发明作者:Eric Rambaud；Denis Brossard；Frederic RIDRAY；Philippe Descamps；Xavier Bardey；Stephane Le Clainche
    申请人:Airbus Operations SAS；Airbus SAS；
    IPC主号:
    专利说明:

    TURBOREACTOR COMPRISING A PLATFORM EQUIPPED WITH A
    REVERSING SYSTEM COMPRISING EXTERNAL DOORS AND
    INDOOR
    TECHNICAL AREA
    The present invention relates to a turbofan engine which comprises a nacelle equipped with a reversing system comprising exterior and interior doors, as well as an aircraft comprising at least one such turbofan engine.
    STATE OF THE PRIOR ART
    An aircraft has a fuselage on each side of which is attached a wing. Under each wing is suspended at least one turbofan engine with a secondary stream. Each turbofan is fixed under the wing by means of a mast which is fixed between the structure of the wing and the structure of the turbofan.
    The turbofan has a motor and a nacelle which is fixed around the engine to delimit between them a secondary stream.
    The nacelle has a reversing system that includes a plurality of interior doors, each of which is movable between a stored position in which it is pressed against an interior surface of the nacelle around the secondary vein, and a deployed position in which it is positioned in through the secondary vein to direct the secondary flow towards a cleared window in the nacelle by the displacement of the interior door.
    It is interesting to be able to find a thrust reversal system which is optimized and implemented by a simple mechanism.
    STATEMENT OF THE INVENTION
    An object of the present invention is to provide a double-flow turbojet engine which comprises a nacelle equipped with a reversing system with a plurality of exterior and interior doors and with a different opening / closing mechanism.
    To this end, a double-flow turbojet engine is proposed comprising a motor, a nacelle surrounding the motor and a fan casing, where a secondary stream of a secondary flow is delimited between the nacelle and the motor and in which an air flow flows in a direction of flow, said nacelle comprising:
    - a fixed structure attached to the fan casing,
    - an inverter system presenting:
    a mobile assembly having a frame and a movable cover fixed to the frame, the movable assembly being movable in translation on the fixed structure in a direction of translation between an advanced position in which the movable assembly is positioned so that the movable hood is brought closer to the fan casing and a retracted position in which the movable assembly is positioned so that the movable hood is moved away from the blower casing to define between them an open window between the secondary stream and the exterior of Platform,
    - a plurality of pairs of doors, each pair being formed by an interior door and an exterior door disposed opposite the interior door,
    - for each pair of doors, a slide mounted movable in translation parallel to the direction of translation on the frame between a first position and a second position, where each door of a couple is articulated by a rear edge on the associated slide, between a stored position in which it closes a window area and a deployed position in which it does not close said window area, the interior doors extending towards the motor in the deployed position, the exterior doors extending towards the outside of the nacelle in the deployed position,
    - For each slide, a first transmission system provided for passing the interior door associated with the slide, from the stored position to the deployed position simultaneously with the passage of the slide from the first position to the second position and vice versa, and a second system of transmission provided for passing the outer door associated with the slide, from the stored position to the deployed position simultaneously with the passage of the slide from the first position to the second position and vice versa, and
    at least one first actuator provided to move the frame in translation from the advanced position to the retracted position and vice versa, and
    - For each slide, a second actuator partially fixed to the frame and designed to ensure the translational movement of the slide from the first position to the second position and vice versa.
    Such a turbojet engine makes it possible to optimize the thrust reverser by installing internal and external doors, to simplify the mechanism actuating the reversing system and to dissociate the movement of the mobile assembly from the movement of the internal and external doors.
    Advantageously, the frame comprises two rods arranged across the window and extending parallel to the direction of translation, and for each rod, the slide has a bore in which said rod is fitted.
    Advantageously, the first transmission system comprises at least a first rod articulated by one end to the interior door and articulated by another end to the frame.
    Advantageously, the first transmission system comprises two first rods arranged on either side of a median plane of the interior door.
    Advantageously, the articulation at the level of the frame is arranged in front with respect to the articulation of the first rod to the interior door.
    Advantageously, the second transmission system comprises at least a second rod articulated by one end to the external door and articulated by another end to the frame.
    Advantageously, the second transmission system comprises two second rods arranged on either side of a median plane of the outer door.
    Advantageously, the articulation at the level of the frame is arranged in front with respect to the articulation of the second rod to the external door.
    Advantageously, the exterior doors are arranged between the movable cover and the fixed structure in the stored position so as to constitute an exterior wall of the nacelle.
    The invention also provides an aircraft comprising at least one turbofan engine according to one of the preceding variants.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
    Fig. 1 is a side view of an aircraft comprising a turbofan engine according to the invention, FIG. 2 is a perspective view from the inside of a part of a nacelle of the turbofan engine according to the invention, FIG. 3 is a schematic representation in section of an inverter system according to the invention in the advanced and stored position, FIG. 4 is a representation similar to that of FIG. 3 for an intermediate position corresponding to a retracted and stored position, FIG. 5 is a representation similar to that of FIG. 3 for a retracted and deployed position, and FIG. 6 shows an external view of the reversing system.
    DETAILED DESCRIPTION OF EMBODIMENTS
    In the following description, the terms relating to a position are taken with reference to the direction of advance of the aircraft and the flow of air in the turbojet engine therefore flows from the front to the rear of the aircraft. aircraft while the aircraft is moving forward.
    Fig. 1 shows an aircraft 10 which has a fuselage 12 on each side of which is fixed a wing 14 which carries at least one turbofan 100 according to the invention. The turbofan 100 is fixed under the wing 14 by means of a mast 16.
    The turbofan 100 has a nacelle 102, a motor which is housed inside the nacelle 102 in the form of a core and a fan casing 206a in front of the nacelle 102.
    In the description which follows, and by convention, X is called the longitudinal axis of the turbofan 100 which is parallel to the longitudinal axis of the aircraft 10 oriented positively towards the front of the aircraft 10, we call Y the transverse axis which is horizontal when the aircraft is on the ground, and Z the vertical axis, these three directions X, Y and Z being orthogonal to one another.
    Fig. 2 shows part of the nacelle 102 and FIGS. 3 to 5 show different positions of an inverter system 250 of the nacelle 102. FIG. 6 shows an external view of the reversing system 250 in the retracted and deployed position, but where only an external door 105 is shown diagrammatically by dashed lines.
    The turbofan 100 has between the nacelle 102 and the engine, a secondary stream 202 in which circulates the secondary stream 208 coming from the air inlet through the blower and which therefore flows in the direction of flow which goes from front to back of pod 102.
    The nacelle 102 has a fixed structure 206 which is fixedly mounted on the fan casing 206a.
    The reversing system 250 has a movable assembly 207 which comprises a movable cover 207a forming the walls of the nozzle and a frame 207b. The frame 207b here takes the form of a cylinder with perforated walls. The movable cover 207a is fixed to and at the rear of the frame 207b.
    The movable assembly 207, via the frame 207b, is mounted movable in translation in a direction of translation generally parallel to the longitudinal axis X on the fixed structure 206 of the nacelle 102, and more particularly here on the 12-hour beam and the beam 6 hours.
    The translation of the frame 207b, and therefore of the mobile assembly 207, is carried out by any suitable slide system such as for example slides between the fixed structure 206 and the frame 207b.
    The movable assembly 207, and therefore the frame 207b, is movable between an advanced position (Fig. 3) and a retracted position (Figs 4, 5 and 6) and vice versa. In the advanced position, the movable assembly 207, and therefore the frame 207b, is positioned as far forward as possible relative to the longitudinal axis X so that the movable cover 207a is brought closer to the fan casing 206a. In the retracted position, the movable assembly 207, and therefore the frame 207b, is positioned as far back as possible relative to the longitudinal axis X so that the movable cover 207a is distant towards the rear of the fan casing 206a.
    In the advanced position, the movable cover 207a and the fan casing 206a extend so as to define the outer surface of the secondary stream 202.
    In the retracted position, the movable cover 207a and the fan casing 206a are at a distance and define between them a window 210 open between the secondary stream 202 and the outside of the nacelle 102. That is to say that the air coming from the secondary flow 208 crosses the window 210 to join the exterior of the double flow turbojet 100.
    The fan casing 206a delimits the window 210 in front with respect to the longitudinal axis X and the movable cover 207a delimits the window 210 in rear with respect to the longitudinal axis X.
    The nacelle 102 has a plurality of interior doors 104 distributed over the periphery and inside the nacelle 102 as a function of the angular opening of the window 210 around the longitudinal axis X.
    Each interior door 104 is hinged on a slide 214 between a stored position (Figs. 3 and 4) and a deployed position (Fig. 5) and vice versa. The passage from the stored position to the deployed position is effected by a rotation of the interior door 104 towards the interior of the turbojet 100. The articulation takes place along a rear edge of the interior door 104 while the front edge of interior door 104 moves.
    The stored position of the interior doors 104 can be adopted when the frame 207b is in the advanced position or in the retracted position. The deployed position of the interior doors 104 can only be adopted when the frame 207b is in the retracted position.
    In the stored position, each interior door 104 closes an area of the openwork part of the frame 207b when the latter is in the advanced position and the same area of the openwork part of the frame 207b and an area of the window 210 when the frame 207b is in position steephead Valley. In the deployed position, the interior door 104 does not close said zone of the window 210 nor the perforated part of the frame 207b allowing the passage of the secondary flow 208 and the interior door 104 extends towards the motor, that is to say say across the secondary vein 202.
    Thus, in the stored and advanced position, each interior door 104 is positioned outside the fan casing 206a and in the deployed position, each interior door 104 is positioned across the secondary stream 202 and deflects at least part of the secondary flow. 208 outwards through the window 210, the flow is directed towards the front using external doors 105 making it possible to produce a counter-thrust and described below.
    Each interior door 104 is articulated by its rear edge to the slider 214 on hinges 212 fixed to the slider 214 while the opposite front edge is free and is positioned forward in the stored position and towards the motor in the deployed position.
    The reversing system 250 also includes, for each interior door 104, an exterior door 105. The exterior doors 105 are distributed on the periphery and outside of the nacelle 102 according to the angular opening of the window 210 around the longitudinal axis X. The exterior doors 105 are arranged outside with respect to the interior doors 104. Each exterior door 105 is mounted facing an interior door 104 and the exterior door 105 and the interior door 104 facing each other constitute a pair of doors. The reversing system 250 thus comprises a plurality of pairs of doors 104, 105 arranged inside the nacelle 102.
    Each outer door 105 is mounted articulated on the slide 214 between a stored position (Figs. 3 and 4) and a deployed position (Fig. 5) and vice versa. The passage from the stored position to the deployed position is effected by a rotation of the external door 105 towards the outside of the turbojet 100. The articulations of the external doors 105 are generally opposite the articulations of the internal doors 104, thus as is shown in Fig. 5, when the interior doors 104 and the exterior doors 105 are deployed, they generally form a continuity.
    The stored position of the exterior doors 105 can be adopted when the frame 207b is in the advanced position or in the retracted position. The deployed position can only be adopted when the frame 207b is in the retracted position. The deployed position, respectively stored, of the exterior doors 105 is synchronized with the deployed position, respectively stored, of the interior doors 104.
    In the stored position, each outer door 105 closes an area of the perforated part of the frame 207b when the latter is in the advanced position and the same area of the perforated part of the frame 207b and a zone of the window 210 when the frame 207b is in position steephead Valley. In the deployed position, the outer door 105 does not close said zone of the window 210 nor the perforated part of the frame 207b and extends towards the outside of the nacelle 102 allowing the passage of the secondary flow 208.
    Thus, in the stored and advanced position, each exterior door 105 is generally in the extension of the movable cover 207a outside the fan casing 206a and in the deployed position, each exterior door 105 opens outward and deflects the part secondary flow 208 which has been previously diverted by the interior doors 104 through the window 210.
    In the stored position, the exterior doors 105 are arranged between the movable cover 207a and the fixed structure 206 so as to constitute an exterior wall of the nacelle 102 which is therefore in contact with the air flow which flows around the nacelle 102.
    Each outer door 105 is articulated by a rear edge to the slider 214 on hinges 213 fixed to the slider 214 while the opposite front edge is free and is positioned forward in the stored position and outward in the deployed position.
    For each pair of doors 104, 105, the reversing system 250 therefore has a slider 214 associated with said pair of doors 104, 105. The slider 214 is mounted movable in translation in a direction parallel to the direction of translation on the frame 207b. The slider 214 is thus movable between a first position which corresponds to the stored position and a second position which corresponds to the deployed position. Each door 104, 105 is thus articulated on the slide 214 and is therefore independent of the movable cover 207 and it is not attached to it.
    The passage from the first position to the second position of the slider 214 is mechanically associated with the passage from the stored position to the deployed position of each door 104, 105 and vice versa.
    In the particular embodiment presented here, the reversing system 250 also has, for each slider 214, a first transmission system 216 which is provided for passing the interior door 104 associated with the slider 214, from the stored position to the deployed position. simultaneously, at the passage of the slider 214 from the first position to the second position in order to open the interior door 104 and vice versa.
    In the same way, the reversing system 250 also has, for said slider 214, a second transmission system 217 which is provided for passing the outer door 105 associated with the slider 214, from the stored position to the simultaneously deployed position, in passing of the slider 214 from the first position to the second position in order to open the outer door 105 and vice versa.
    In the embodiment of the invention presented here, to reach the first position, the slider 214 is moved backwards while to reach the second position, the slider 214 is moved forward.
    The translation of the slide 214 on the frame 207b is carried out by any suitable slide system such as, for example, that which is described below.
    The transition from the advanced position of the frame 207b to the retracted position of the frame 207b and deployed from the interior doors 104 and the exterior doors 105 therefore consists, from the advanced position of the frame 207b and therefore from the stored positions of the interior doors 104 and exterior 105, to move the frame 207b back by translation relative to the front frame 206 to reach the retracted position for the frame 207b and the stored positions of the interior 104 and exterior doors 105, then to move each slider 214 from the first position to the second position , that is to say forward, to pass the interior doors 104 and the exterior doors 105 from the stored position to the deployed position.
    Reverse movement returns to the advanced position.
    The nacelle 102 also includes a set of actuators 218 and 220 ensuring the movement in translation of the frame 207b and of the slide 214. Each actuator 218, 220 is controlled by a control unit, for example of the processor type, which controls the movements in one way or the other depending on the needs of the aircraft 10.
    Each actuator 218, 220 can take, for example, the form of an electric ball cylinder or any other type of suitable cylinder.
    To ensure the displacement of the frame 207b, the nacelle 102 comprises at least a first actuator 218 fixed for a part to the fixed structure 206 of the nacelle 102 and for a part to the frame 207b. Each first actuator 218 is thus provided to ensure, from the advanced position of the frame 207b and therefore the stored positions of the interior 104 and exterior doors 105, a movement in translation of the frame 207b to the retracted position, and vice versa. When moving the frame 207b, each slider 214 which is carried by the frame 207b follows the same movement.
    Here, the cylinder of the first actuator 218 is fixed to the fixed structure 206 and the movable rod of the first actuator 218 is fixed to the frame 207b.
    To ensure the movement of each slide 214, and therefore of each interior 104 and exterior 105 door, the reversing system 250 comprises, for each slide 214, a second actuator 220 which is fixed for part to the frame 207b and for part to the slide 214. The second actuator 220 is provided to move the slide 214 in translation from the first position to the second position.
    Here the cylinder of the second actuator 220 is fixed to the frame 207b and the movable rod of the second actuator 220 is fixed to the slide 214.
    The second actuator 220 is separate from each first actuator 218 and they can therefore be moved independently of each other. The displacement of the mobile assembly 207 from the advanced position to the retracted position is dissociated from the displacement of the doors 104 and 105.
    Fig. 6 shows an external view of the nacelle 102 which shows the slide system between the frame 207b and the slide 214.
    To make the slide system, the frame 207b has two rods 602 arranged across the window 210 and extending parallel to the direction of translation. For each rod 602, 604, the slider 214 has a bore in which said rod 602, 604 is fitted, which allows the slider 214 to move along the rods 602 and 604.
    The first transmission system 216 comprises at least a first rod articulated by one end to the interior door 104 and articulated by another end to the movable assembly 207 and more particularly to a part of the frame 207b disposed in front with respect to the articulation of the first rod to the interior door 104.
    For balancing reasons, the first transmission system 216 comprises two first rods arranged on either side of a median plane of the interior door 104 and passing through the longitudinal axis X.
    The second transmission system 217 comprises at least a second rod articulated by one end to the external door 105 and articulated by another end to the mobile assembly 207 and more particularly to a part of the frame 207b disposed in front with respect to the articulation of the second rod to the outer door 105.
    Likewise, for balancing reasons, the second transmission system 217 comprises two second rods arranged on either side of a median plane of the outer door 105 and passing through the longitudinal axis X as is shown in Fig. 6.
    The invention has been more particularly described in the case of a nacelle under a wing but it can be applied to a nacelle located at the rear of the fuselage.
    To better control the secondary flow 208, the nacelle 102 includes at least one deflector 226 (if there are several, then a cascade type grid) which is arranged around the secondary vein 202 at the level of the entry of window 210, that is to say generally at the level of the zone of passage of the secondary vein 202 to window 210 in an area where the flow has the most difficulty in turning to create reverse thrust (i.e. towards the front of the nacelle).
    Each deflector 226 is fixed to the mobile assembly 207 of the nacelle 102.
    Each deflector 226 takes the form of a fin which directs the secondary flow 208 towards the window 210 then towards the front of the double-flow turbojet 100. In the embodiment of the invention presented here, in the closed position, each deflector
    226 is housed in the fixed structure 206 between the exterior door 105 and the interior door 104.
    In the embodiment of the invention presented in FIG. 6, the deflectors 226 are arranged between the rods 602 and 604.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1) Double-flow turbojet engine (100) comprising an engine, a nacelle (102) surrounding the engine and a fan casing, where a secondary stream (202) of a secondary flow (208) is delimited between the nacelle (102) and the motor and in which an air flow circulates in a direction of flow, said nacelle (102) comprising:
    - a fixed structure (206) attached to the fan casing (206a),
    - an inverter system (250) having:
    - A mobile assembly (207) having a frame (207b) and a movable cover (207a) fixed to the frame (207b), the mobile assembly (207) being movable in translation on the fixed structure (206) in a direction of translation between an advanced position in which the movable assembly (207) is positioned so that the movable cover (207a) is brought closer to the fan casing (206a) and a retracted position in which the movable assembly (207) is positioned so that the movable cover (207a) is remote from the fan casing (206a) to define between them a window (210) open between the secondary stream (202) and the outside of the nacelle (102),
    a plurality of pairs of doors, each pair being formed by an interior door (104) and an exterior door (105) disposed opposite the interior door (104),
    - For each pair of doors (104, 105), a slide (214) mounted movable in translation parallel to the direction of translation on the frame (207b) between a first position and a second position, where each door (104, 105) of a torque is mounted articulated by a rear edge on the associated slide (214), between a stored position in which it closes an area of the window (210) and a deployed position in which it does not close said area of the window (210), the interior doors (104) extending towards the motor in the deployed position, the exterior doors (105) extending towards the exterior of the nacelle (102) in the deployed position,
    - For each slide (214), a first transmission system (216) provided for passing the interior door (104) associated with the slide (214), from the stored position to the deployed position simultaneously, at the passage of the slide (214) from the first position to the second position and vice versa, and a second transmission system (217) provided for passing the outer door (105) associated with the slide (214), from the stored position to the deployed position simultaneously with the passage of the slide (214) from the first position to the second position and vice versa, and
    - at least one first actuator (218) provided to move the frame in translation (207b) from the advanced position to the retracted position and vice versa, and
    - For each slide (214), a second actuator (220) partially fixed to the frame (207b) and provided to ensure the displacement in translation of the slide (214) from the first position to the second position and vice versa.
    [2" id="c-fr-0002]
    2) turbofan engine (100) according to claim 1, characterized in that the frame (207b) comprises two rods (602, 604) arranged across the window (210) and extending parallel to the direction of translation, and in that for each rod (602, 604), the slide (214) has a bore in which said rod (602, 604) is fitted.
    [3" id="c-fr-0003]
    3) turbofan (100) according to one of claims 1 or 2, characterized in that the first transmission system (216) comprises at least a first rod articulated by one end to the inner door (104) and articulated by another end to the frame (207b).
    [4" id="c-fr-0004]
    4) turbofan (100) according to claim 3, characterized in that the first transmission system (216) comprises two first rods arranged on either side of a median plane of the interior door (104).
    [5" id="c-fr-0005]
    5) turbofan (100) according to one of claims 3 or 4, characterized in that the articulation at the level of the frame (207b) is arranged in front with respect to the articulation of the first rod to the interior door (104).
    [6" id="c-fr-0006]
    6) turbofan engine (100) according to one of claims 1 to 4, characterized in that the second transmission system (217) comprises at least a second rod articulated by one end to the outer door (105) and articulated by another end to the frame (207b).
    [7" id="c-fr-0007]
    7) turbofan engine (100) according to claim 6, characterized in that the second transmission system (217) comprises two second rods arranged on either side of a median plane of the outer door (105).
    [8" id="c-fr-0008]
    8) turbofan (100) according to one of claims 6 or 7, 5 characterized in that the articulation at the level of the frame (207b) is arranged in front with respect to the articulation of the second rod to the door exterior (105).
    [9" id="c-fr-0009]
    9) turbofan (100) according to one of claims 1 to 8, characterized in that the outer doors (105) are arranged between the movable cover (207a) and the fixed structure (206) in the stored position so as to build a wall
    10 exterior of the nacelle (102).
    [10" id="c-fr-0010]
    10) Aircraft (10) comprising at least one turbofan engine (100) according to one of the preceding claims.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3078111B1|2020-01-17|
    US20190257269A1|2019-08-22|
    EP3530925A1|2019-08-28|
    CN110182371A|2019-08-30|
    EP3530925B1|2020-12-16|
    引用文献:
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    US20210094697A1|2019-09-30|2021-04-01|Rohr, Inc.|Linkage between inner and outer cowl doors|
    法律状态:
    2019-02-20| PLFP| Fee payment|Year of fee payment: 2 |
    2019-08-23| PLSC| Publication of the preliminary search report|Effective date: 20190823 |
    2020-02-19| PLFP| Fee payment|Year of fee payment: 3 |
    2021-11-12| ST| Notification of lapse|Effective date: 20211005 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1851556A|FR3078111B1|2018-02-22|2018-02-22|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH A REVERSING SYSTEM COMPRISING EXTERNAL AND INTERIOR DOORS|
    FR1851556|2018-02-22|FR1851556A| FR3078111B1|2018-02-22|2018-02-22|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH A REVERSING SYSTEM COMPRISING EXTERNAL AND INTERIOR DOORS|
    EP19153410.6A| EP3530925B1|2018-02-22|2019-01-24|Turbine engine comprising a nacelle provided with a reverser system comprising outer and inner doors|
    US16/280,593| US20190257269A1|2018-02-22|2019-02-20|Turbojet engine comprising a nacelle equipped with a thrust-reversing system comprising outer and inner doors|
    CN201910125996.1A| CN110182371A|2018-02-22|2019-02-20|Turbojet and aircraft|
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