• 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 engine (100) comprising a fan casing (20) and a nacelle (102) comprising a cowl movable in translation between an advanced position and a retracted position in which the movable cowl and the fan casing ( 20) define between them a window (210). The nacelle (102) also comprises reversing flaps (104), each being articulated on the moving assembly (207) between a closed position in which it closes the window (210) and an open position in which it does not close the window (210). The nacelle (102) also has a drive mechanism (250) comprising a lever arm (252) rotatable on the moving assembly (207) and having a roller (256), a rod (254) mounted movably in rotation between the inverter flap (104) and the lever arm (252), and a groove (258) receiving said roller (256), said groove (258) having a front portion parallel to the translation direction and a rear portion extending in front of the front and facing inwards, moving forward from front to back.
    公开号:FR3068394A1
    申请号:FR1756037
    申请日:2017-06-29
    公开日:2019-01-04
    发明作者:Olivier Pautis；Laurent Tizac；Frederic RIDRAY；Lionel Czapla；Frederic Piard
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS
    TECHNICAL AREA
    The present invention relates to a turbofan engine which comprises a nacelle equipped with reversing flaps, 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. 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 motor.
    The nacelle comprises a plurality of reversing flaps, each being movable between a closed position in which it comes in continuity with the external surface of the nacelle and an open position in which it opens a window in the wall of the nacelle to expel the air secondary flow to the outside.
    The reversing flap is mounted so that it can rotate on the structure of the nacelle so as to pass from a closed position where the reversing flap does not close the stream of the secondary flow to an open position where the reversing flap closes the stream.
    Thus, in the open position, the reversing flap diverts part of the secondary flow outward through the window.
    The movement of each reversing flap is controlled by one or more actuators which are relatively heavy.
    Although the mechanism of such a reversing flap is entirely satisfactory, it is desirable to find different mechanisms.
    STATEMENT OF THE INVENTION
    An object of the present invention is to provide a double-flow turbojet engine which includes a nacelle equipped with reversing flaps with a different opening mechanism.
    For this purpose, there is proposed a turbofan engine comprising a motor and a nacelle surrounding the engine which comprises a fan casing and a core disposed inside the fan casing, where a stream of a secondary flow is delimited between the core and the fan casing, said nacelle comprising:
    - a fixed structure,
    - a fan cover fixedly mounted on the fixed structure and a mobile assembly comprising a mobile cover and being movable in translation relative to the fixed structure in a translation direction between an advanced position in which the mobile cover is brought closer to the fan cover and a retracted position in which the movable cover is distant from the fan cover towards the rear,
    - a window defined upstream by the fan cover and downstream by the movable cover, said window being open, in the retracted position, between the vein and the outside of the nacelle,
    a reversing flap mounted on the movable assembly tilting between a closed position in which it closes the window and an open position in which it does not close the window, and
    a drive mechanism provided for coordinating and delaying the passage from the closed position to the open position of the reversing flap with the passage from the advanced position to the retracted position of the movable cover and vice versa, said drive mechanism being designed to achieve a first combination ensuring, from the closed position and the advanced position:
    - a rearward translation of the mobile assembly in the direction of translation to move the mobile assembly from the advanced position to the retracted position passing through an intermediate position, and
    - from the moment when the mobile assembly passes through the intermediate position, a tilting of the reversing flap to move the reversing flap from the closed position to the open position, and the drive mechanism also being provided for making a second combination ensuring , from the open position and the retracted position:
    - a forward translation of the mobile assembly in the direction of translation to move the mobile assembly from the retracted position to the advanced position via the intermediate position, and
    - until the mobile assembly passes through the intermediate position, tilting in the opposite direction of the reversing flap to move the reversing flap from the open position to the closed position, the drive mechanism comprising:
    - a lever arm having a front end and a rear end, where the front end is rotatably mounted on the mobile assembly and where the lever arm has at least one between the front end and the rear end rotating mobile roller,
    a connecting rod having a first end and a second end and where the first end is mounted so as to be able to rotate on the reversing flap and where the second end is mounted to be movable in rotation on the rear end of the lever arm, and
    - For each roller, a groove fixed to the fixed structure and in which said roller is received, said groove having a front part parallel to the direction of translation and a rear part extending following the front part and oriented towards the interior progressing from front to rear, the junction between the first part and the second part taking the form of a bend and where the position of the roller at this bend corresponds to the intermediate position.
    Such a turbojet engine provides better guidance of the reversing flaps.
    Advantageously, the turbofan has two rollers aligned on either side of the lever arm and two grooves of the same shape and parallel to each other, each receiving a roller.
    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 turbojet engine according to the invention, FIG. 2 is a perspective view of the turbojet engine according to the invention, FIGS. 3 to 6 are side views and in section through a median plane of a part of the turbojet engine according to the invention in different positions, and FIG. 7 is a perspective view of a detail of a drive mechanism according to the invention.
    DETAILED DESCRIPTION OF EMBODIMENTS
    In the following description, the terms relating to a position are taken with reference to an aircraft in the advancing position as shown in FIG. 1. In particular, the front and rear positions are taken with reference to the normal direction of advance of the aircraft.
    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.
    Fig. 2 shows a part of the double-flow turbojet engine 100 which has a nacelle 102 and a motor which is housed inside the nacelle 102 and which comprises a fan casing 20 and a core disposed inside the fan casing 20.
    In the following description, and by convention, X is called the longitudinal axis of the turbofan 100 which is parallel to the longitudinal axis of the aircraft 10 or roll axis, oriented positively in the direction of travel of the aircraft 10, Y is called the transverse axis which is parallel to the pitch axis of the aircraft which is horizontal when the aircraft is on the ground, and Z the vertical axis which is parallel to the yaw axis when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to one another and forming an orthonormal reference frame originating from the center of gravity of the turbofan 100.
    Figs. 3 to 6 show part of the nacelle 102.
    As shown in Figs. 2 to 6, the turbofan 100 has between the core and the fan casing 20, a stream 202 in which circulates the secondary flow 208 coming from the air inlet through the blower.
    The nacelle 102 has a fixed structure 206 which here comprises among other things two crowns which are fixed for example at 12 o'clock and 6 o'clock and which carries a fan cover 205 which is fixed.
    The nacelle 102 has a movable assembly 207 which here incorporates cascades 209 allowing the redirection of the flow passing from the interior to the exterior and has a sliding frame 207b and a movable cover 207a secured to the sliding frame 207b and forming the outer walls of nacelle 102. Of course, it is also possible to plan that the waterfalls are absent.
    The sliding frame 207b is perforated and here takes the form of a front crown 21a and a rear crown 211b which are integral. The movable assembly 207, that is to say the movable cover 207a and the sliding frame 207b, are movable in translation in a direction of translation generally parallel to the longitudinal axis X.
    The translation of the mobile assembly 207 is achieved for example by slide systems between the fixed structure 206 and the sliding frame 207b.
    The movable assembly 207 is movable between an advanced position (Figs. 2 and 3) and a retracted position (Fig. 6) and vice versa, Figs. 4 and 5 showing intermediate positions between the advanced position and the retracted position. In the advanced position, the movable assembly 207 is positioned as far forward as possible so that the movable cover 207a is brought closer to the fan cover 205 in order to form aerodynamic continuity. In the retracted position, the movable assembly 207 is positioned as far back as possible so that the movable cover 207a is distant from the fan cover 205 in order to clear a window 210.
    The nacelle 102 also includes an actuation system ensuring the displacement in translation of the mobile assembly 207 from the advanced position to the retracted position and vice versa. The actuation system comprises for example one or more motors or one or more jacks, where each is controlled by a control unit, for example of the processor type, which controls the movements in one direction or the other according to the needs of the aircraft 10. For example, in the case of an actuation system comprising jacks, each is mounted for example between the sliding chassis 207b and the fixed structure of the nacelle 102.
    In the advanced position, the sliding frame 207b, more particularly the rear crown 211b, and the fan casing 20 extend so as to define the outer surface of the stream 202.
    In the retracted position, the sliding frame 207b and the fan casing 20 are at a distance and define between them the window 210 which is open between the vein 202 and the outside of the nacelle 102 here through the cascades 209. That is that is to say that the air coming from the secondary flow 208 crosses the window 210 by crossing the cascades 209 to join the exterior of the double flow turbojet 100.
    In the retracted position, the fan casing 20 and the fan cover 205 delimit the window 210 upstream relative to the longitudinal axis X and the movable cover 207a and here the rear ring 211b delimit the window 210 downstream relative to the longitudinal axis X. The window 210 is located opposite the waterfalls 209.
    The sliding frame 207b carries reversing flaps 104 distributed over the periphery of the nacelle 102 as a function of the angular opening of the window 210 around the longitudinal axis X. Each reversing flap 104 here extends between the front ring 211a and the rear crown 211b, and each is mounted articulated between a closed position (Figs. 2 to 5) and an open position (Fig. 5) and vice versa.
    The closed position can be adopted when the sliding frame 207b is in the advanced position or in the retracted position. The open position can only be adopted when the sliding frame 207b is in the retracted position.
    In the closed position, each reversing flap 104 closes an area of the openwork part of the sliding frame 207b when the latter is in the advanced position and the same area of the openwork part of the sliding frame 207b and a window area 210 when the sliding frame 207b is in the back position. In the open position, the reversing flap 104 does not close either said zone of the window 210 or the perforated part of the sliding frame 207b allowing the passage of the secondary flow 208.
    Thus, in the closed position, each reversing flap 104 is generally in a plane parallel to the axis X and in the open position, each reversing flap 104 is positioned generally in a plane perpendicular to the axis X, across the stream 202 and deflects at least part of the secondary flow 208 outward through the window 210.
    In the advanced position, each reversing flap 104 is positioned outside the fan casing 20.
    Each reversing flap 104 is articulated at the downstream part of the sliding frame 207b, for example, on hinges fixed to the sliding frame 207b, and here more particularly to the rear crown 211b, while the opposite free edge is positioned upstream in closed position and towards the motor in open position. Each reversing flap 104 is thus mounted on the movable assembly 207 rocking about a tilting axis which is generally tangential with respect to the cylindrical shape of the nacelle 102.
    The transition from the closed position to the open position of the reversing flap 104 is coordinated but delayed compared to the transition from the advanced position to the retracted position of the movable assembly 207 and vice versa. When switching from the closed position to the open position, the tilting of the reversing flap 104 begins when the movable assembly 207 passes through an intermediate position (Fig. 5) between the advanced position and the retracted position. Conversely, when switching from the open position to the closed position, the tilting of the reversing flap 104 stops when the movable assembly 207 passes through the intermediate position returning from the retracted position to the advanced position.
    This coordination is ensured by a drive mechanism 250 which performs, from the closed position and the advanced position, a first combination ensuring:
    a rearward translation (arrow 52) of the mobile assembly 207 in the direction of translation from the advanced position to the retracted position passing through the intermediate position, and,
    - from the moment when the mobile assembly 207 passes through the intermediate position, a tilting (arrow 54) of the reversing flap 104 which ensures the displacement of the reversing flap 104 from the closed position to the open position.
    As explained, the rearward translation of the mobile assembly 207 continues during the tilting of the reversing flap 104.
    Conversely, the passage from the open position to the closed position of the reversing flap 104 is ensured by the same drive mechanism 250 which is also provided for producing a second combination ensuring from the open position and the retracted position :
    - a forward translation (arrow 56) of the mobile assembly 207 in the direction of translation from the retracted position to the advanced position passing through the intermediate position, and
    - until the mobile assembly 207 passes through the intermediate position, a tilting (arrow 58) in the opposite direction of the reversing flap 104 which ensures the return of the reversing flap 104 from the open position to the closed position.
    As explained, the forward translation of the movable assembly 207 begins at the same time as the tilting of the reversing flap 104, then the tilting of the reversing flap 104 stops while the translation of the movable assembly 207 is continues. Thus, the movable assembly 207 and the reversing flap 104 move first simultaneously, then from a certain moment, the reversing flap 104 stops and the movable assembly 207 moves alone.
    Fig. 7 shows a detail of the drive mechanism 250.
    The drive mechanism 250 comprises, for each reversing flap 104:
    - A lever arm 252 having a front end and a rear end, where the front end is rotatably mounted on the movable assembly 207, more particularly here on the front ring 211a, and where the lever arm 252 has between the front end and the rear end, at least one roller 256 mounted to move in rotation about a rolling axis,
    a connecting rod 254 having a first end and a second end and where the first end is mounted so as to be able to rotate on the reversing flap 104 and where the second end is mounted to be movable in rotation on the rear end of the lever arm 252, and
    - For each roller 256, a groove 258 fixed to the fixed structure 206 and in which said roller 256 is received, said groove 258 having a front part parallel to the direction of translation and a rear part extending following the part forward and inward, progressing from front to back.
    In the embodiment of the invention presented here, in the closed position, the first end of the connecting rod 254 is in front of the second end so as to form a Z which can be deployed when passing into the open position.
    The junction between the first part and the second part takes the form of a bend and the position of the roller 256 at this bend corresponds to the intermediate position.
    The operation of the drive mechanism 250 is then as follows from the closed position and the advanced position:
    - the mobile assembly 207 and the drive mechanism 250 move in translation (52) rearward (Fig. 3), the roller 256 being in the first part of the groove 258 and being guided by it (Fig. 4) in translation until the turn,
    - when the mobile assembly 207 passes through the intermediate position, the roller 256 reaches the bend and passes into the second part of the groove 258 (FIG. 5),
    - the continuation of the translational movement towards the rear of the mobile assembly 207 and the front end of the lever arm 252, as well as the positioning of the roller 256 guided by the second part of the groove 258 tend to unfold the arm lever 252 and the connecting rod 254 to move the flap 104 (54) to its open position (Fig. 6).
    Conversely, the operation of the drive mechanism 250 is as follows from the open position and the retracted position:
    - the movable assembly 207 and the front end of the lever arm 252 move in translation (56) forwards (Fig. 6) and as long as the roller 256 is guided by the second part of the groove 258, the lever arm 252 and the connecting rod 254 fold back to move the flap 104 (56) to its closed position,
    - when the mobile assembly 207 passes through the intermediate position, the flap 104 is in the closed position and the roller 256 reaches the bend and passes into the first part of the groove 258 (FIG. 5),
    - The displacement in forward translation of the movable assembly 207 and the drive mechanism 250 then continues to the advanced position (Fig. 3) where the roller 256 is guided by the first part of the groove 258 (Fig. 4).
    The axes of rotation of the lever arm 252 and of the connecting rod 254 as well as the axes of bearings relating to the same reversing flap 104, are mutually parallel and generally parallel to the tilting axis of the reversing flap 104.
    In the embodiment of the invention shown in Figs. 2 to 7, there are two rollers 256 which are aligned on either side of the lever arm 252 and therefore there are also two grooves 258 of the same shape and parallel to each other, each receiving a roller 256.
    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.
    权利要求:
    Claims (3)
    [1" id="c-fr-0001]
    1) Double-flow turbojet engine (100) comprising an engine and a nacelle (102) surrounding the engine which comprises a fan casing (20) and a core disposed inside the fan casing (20), where a vein (202 ) of a secondary flow (208) is delimited between the core and the fan casing (20), said nacelle (102) comprising:
    - a fixed structure (206),
    - a fan cover (205) fixedly mounted on the fixed structure (206) and a mobile assembly (207) comprising a mobile cover (207a) and being movable in translation relative to the fixed structure (206) in a direction of translation between an advanced position in which the movable cover (207a) is brought closer to the blower cover (205) and a retracted position in which the movable cover (207a) is removed from the blower cover (205) towards the rear,
    - A window (210) delimited upstream by the fan cover (205) and downstream by the movable cover (207a), said window (210) being open, in the retracted position, between the vein (202) and the outside nacelle (102),
    - a reversing flap (104) mounted on the mobile assembly (207) tilting between a closed position in which it closes the window (210) and an open position in which it does not close the window (210), and
    a drive mechanism (250) provided for coordinating and delaying the passage from the closed position to the open position of the reversing flap (104) with the passage from the advanced position to the retracted position of the movable cover (207) and vice versa, said drive mechanism (250) being designed to produce a first combination ensuring, from the closed position and the advanced position:
    - a rearward translation (52) of the mobile assembly (207) in the direction of translation to move the mobile assembly (207) from the advanced position to the retracted position via an intermediate position, and
    - from the moment when the mobile assembly (207) passes through the intermediate position, a tilting (54) of the reversing flap (104) to move the reversing flap (104) from the closed position to the open position, and the mechanism drive (250) also being provided for making a second combination ensuring, from the open position and the retracted position:
    - a forward translation (56) of the mobile assembly (207) in the direction of translation to move the mobile assembly (207) from the retracted position to the advanced position via the intermediate position, and
    - until the mobile assembly (207) passes through the intermediate position, a tilting (58) in the opposite direction of the reversing flap (104) to move the reversing flap (104) from the open position to the closed position, the drive mechanism (250) comprising:
    - A lever arm (252) having a front end and a rear end, where the front end is rotatably mounted on the mobile assembly (207) and where the lever arm (252) has between the front end and the rear end, at least one roller (256) movable in rotation,
    - a connecting rod (254) having a first end and a second end and where the first end is mounted mobile in rotation on the reversing flap (104) and where the second end is mounted mobile in rotation on the rear end of the lever arm (252), and
    - For each roller (256), a groove (258) fixed to the fixed structure (206) and in which is received said roller (256), said groove (258) having a front part parallel to the direction of translation and a part rear extending following the front part and oriented inwards progressing from front to rear, the junction between the first part and the second part taking the form of a bend and where the position of the roller (256) at this bend corresponds to the intermediate position.
    [2" id="c-fr-0002]
    2) turbofan (100) according to claim 1, characterized in that it comprises two rollers (256) aligned on either side of the lever arm (252) and in that it has two grooves (258 ) of the same shape and parallel to each other, each receiving a roller (256).
    [3" id="c-fr-0003]
    3) Aircraft (10) comprising at least one turbofan engine (100) according to one of claims 1 or 2.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP1239139B1|2005-12-14|Thrust reverser actuating system in a turbojet engine
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    CA2204589C|2003-09-30|Jet turbine engine thrust reverser employing doors fitted with deflector vanes
    FR3067760B1|2019-06-28|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS
    EP3530925B1|2020-12-16|Turbine engine comprising a nacelle provided with a reverser system comprising outer and inner doors
    EP0882881A1|1998-12-09|Doors with optimally deployable spoilers for a jet engine thrust reverser
    FR3064308A1|2018-09-28|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS
    FR3098862A1|2021-01-22|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES FOR CLOSING THE SECONDARY FLOW VEIN
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    EP3715613A1|2020-09-30|Dual-flow turbojet engine comprising a series of rotary strips for blocking the secondary flow stream
    EP0807752B1|2003-08-13|Thrust reverser of the pivoting door type with a moveable liner pannel
    EP3354577B1|2019-03-27|Turbojet nacelle comprising a thrust reverser flap
    FR3092145A1|2020-07-31|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES TO CLOSE THE SECONDARY FLOW VEIN
    EP3530926B1|2020-12-23|Turbojet nacelle comprising an inverter flap
    EP3379068B1|2019-05-15|Turbojet nacelle comprising an inverter flap
    FR3074854A1|2019-06-14|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH AN INVERTER SYSTEM COMPRISING DOORS
    EP3670883A1|2020-06-24|Turbojet nacelle comprising an inverter flap and a delayed deployment system
    EP3845753A1|2021-07-07|Turbofan engine having a system for sealing the bypass flow passage comprising fabric panels
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    EP3845754A1|2021-07-07|Turbofan engine comprising a system for sealing the bypass flow passage comprising a flexible element
    FR3089206A1|2020-06-05|NACELLE OF A TURBOREACTOR COMPRISING A REVERSING SHUTTER AND A DELAYED DEPLOYMENT SYSTEM
    FR3104211A1|2021-06-11|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES TO CLOSE THE SECONDARY FLOW VEIN
    FR3066232A1|2018-11-16|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER
    FR3077606A1|2019-08-09|NACELLE OF A TURBOJET ENGINE COMPRISING AN EXTERIOR DOOR OF INVERSION
    FR3057617A1|2018-04-20|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER
    同族专利:
    公开号 | 公开日
    EP3421771A1|2019-01-02|
    CN109209677B|2020-12-08|
    FR3068394B1|2019-07-19|
    CN109209677A|2019-01-15|
    US20190003421A1|2019-01-03|
    EP3421771B1|2019-08-14|
    US10550796B2|2020-02-04|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3511055A|1968-05-29|1970-05-12|Rohr Corp|Thrust reverser|
    US3600894A|1970-04-28|1971-08-24|Rohr Corp|Thrust reversing apparatus|
    US20010010148A1|2000-01-27|2001-08-02|Michel Christian Marie Jean|Thrust reverser having a bypass vane-cascade and fitted with a stationary rear structure|
    EP3181882A1|2015-12-18|2017-06-21|Rohr, Inc.|Translating cascade thrust reverser with control of blocker door|
    JPH0717238B2|1983-07-14|1995-03-01|ユナイテツド・テクノロジ−ズ・コ−ポレイシヨン|Gas turbine engine with load sharing adapter|
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    US9188026B2|2008-11-26|2015-11-17|Mra Systems, Inc.|Apparatus for facilitating access to a nacelle interior and method of assembling the same|
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    US10399687B2|2015-12-03|2019-09-03|The Boeing Company|Methods and apparatus to vary an air intake of aircraft engines|
    FR3067406B1|2017-06-13|2019-07-12|Airbus Operations|THRUST INVERTER SYSTEM HAVING LIMITED AERODYNAMIC DISTURBANCES|US10837404B2|2018-07-10|2020-11-17|Rohr, Inc.|Thrust reverser with blocker door system|
    FR3090579A1|2018-12-20|2020-06-26|Airbus Operations|NACELLE OF A TURBOREACTOR COMPRISING A REVERSING SHUTTER AND A DELAYED DEPLOYMENT SYSTEM|
    CN112607037A|2020-12-17|2021-04-06|广州奇典皮件有限公司|Aircraft engine suspension device|
    法律状态:
    2019-01-04| PLSC| Publication of the preliminary search report|Effective date: 20190104 |
    2019-06-19| PLFP| Fee payment|Year of fee payment: 3 |
    2021-03-12| ST| Notification of lapse|Effective date: 20210206 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1756037|2017-06-29|
    FR1756037A|FR3068394B1|2017-06-29|2017-06-29|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS|FR1756037A| FR3068394B1|2017-06-29|2017-06-29|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS|
    EP18177591.7A| EP3421771B1|2017-06-29|2018-06-13|Turbo engine comprising a nacelle with thrust reverser flaps|
    US16/017,634| US10550796B2|2017-06-29|2018-06-25|Turbojet engine comprising a nacelle equipped with reverser flaps|
    CN201810699225.9A| CN109209677B|2017-06-29|2018-06-29|Turbofan engine and aircraft|
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