• 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 nacelle (102) comprising: - a fixed structure carrying a fixed cover (206) and a movable cover (207), the movable cover (207) being movable in translation between a closed position and a position of opening ; - an inverter flap (104) rotatably mounted on the nacelle between a closed position and an open position; and a drive mechanism (300) for the reverser flap (104) and the movable cowl between, respectively, said closed / closed position and said open / open position of the reversing flap / movable cowl, and vice versa, said spring opening mechanism; drive (300) comprising at least one actuator (304) fixed on the one hand to the stationary structure of the nacelle (102) and on the other hand to a fitting (301) fixed to the movable cowl, The driving mechanism ( 300) further comprising, for each actuator (304), resilient means (320) having a first end (321a) attached to the fixed structure of the nacelle (102) and a second end attached to the fitting (301).
    公开号:FR3062637A1
    申请号:FR1751003
    申请日:2017-02-07
    公开日:2018-08-10
    发明作者:Eric Haramburu；Eric Masson；Patrick Oberle
    申请人:Airbus Operations SAS；Airbus SAS；
    IPC主号:
    专利说明:

    Holder (s): AIRBUS OPERATIONS (S.A.S.) Simplified joint-stock company, AIRBUS (S.A.S.) Simplified joint-stock company.
    Extension request (s)
    Agent (s): AIRBUS OPERATIONS SAS Limited company.
    (54) TURBOREACTOR NACELLE HAVING A PUSH.
    INVERTER DRIVE MECHANISM
    FR 3,062,637 - A1 (5y The invention relates to a nacelle (102) comprising:
    - A fixed structure carrying a fixed cover (206) and a mobile cover (207), the mobile cover (207) being movable in translation between a closed position and an open position;
    - a reversing flap (104) mounted to rotate on the nacelle between a closed position and an open position; and
    - a drive mechanism (300) of the reversing flap (104) and of the movable cover between, respectively, said closed / closed position and said open / open position of the reversing flap / movable cover and vice versa, said mechanism drive (300) comprising at least one actuator (304) fixed on the one hand to the fixed structure of the nacelle (102) and on the other hand to a fitting (301) fixed to the movable cover,
    The drive mechanism (300) further comprising, for each actuator (304), an elastic means (320) having a first end (321a) fixed to the fixed structure of the nacelle (102) and a second end fixed to the fitting (301).
    102
    301.
    304b i

    i
    TURBOREACTOR NACELLE INCLUDING A DRIVE INVERTER DRIVE MECHANISM
    TECHNICAL AREA
    The present invention relates to a nacelle of a turbofan engine which comprises at least one thrust reverser and a drive mechanism for said reverser.
    STATE OF THE PRIOR ART
    A nacelle comprises a thrust reverser composed of a movable cover mounted movable in translation on the structure of the nacelle and at least one reversing flap which is mounted rotatably mounted on the structure of the nacelle and which is mechanically linked to the cover mobile.
    The activation of the thrust reverser consists of a displacement, via at least one actuator articulated on the movable cover, of the movable cover towards the rear of the nacelle to cause the reversing flap to tilt until the latter closes in part the secondary flow stream to expel part of the secondary air flow to the outside.
    The aerodynamic pressures on the reversing flap or the mobile hood are high and tend to move the mobile hood towards the rear of the nacelle. The actuator (s) allowing the activation / deactivation of the thrust reverser must be dimensioned accordingly to exert a sufficient tensile force on the movable hood in order to oppose the significant forces induced by the aerodynamic pressures, in particular during deactivation of the inverter.
    In an aircraft where the available power is limited (hydraulic or electric depending on the actuator technology used), the high power requirements of large actuators during the few seconds of their operation to deactivate the thrust reverser are not fully satisfied and the deactivation times of the thrust reverser are therefore not optimal.
    There is a need to decrease the deactivation time of the thrust reverser.
    STATEMENT OF THE INVENTION
    An object of the present invention is to meet the above-mentioned need.
    To this end, a nacelle is proposed for a dual-flow turbojet, said nacelle comprising:
    a fixed structure carrying a fixed cover and a mobile cover, the mobile cover being movable in translation between a closed position in which the mobile cover is brought closer to the fixed cover and an open position in which the mobile cover is remote from the cover fixed,
    - a through opening defined upstream by the fixed cover and downstream by the movable cover in its open position;
    an inverting flap mounted to move in rotation about an axis of rotation between a closed position in which said flap closes the opening and an open position in which said flap does not close the opening,
    a drive mechanism for the reversing flap and the movable cover between, respectively, said closed / closing position and said open / opening position for the reversing flap / movable cover and vice versa, said driving mechanism comprising at least one actuator fixed on the one hand to the fixed structure of the nacelle and on the other hand to a fitting fixed to the movable cover, the drive mechanism further comprising, for each actuator, an elastic means having a first end fixed to the fixed structure of the nacelle and a second end fixed to the fitting.
    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 attached figures, among which:
    Figure 1 is a side view of an aircraft comprising a nacelle according to the invention;
    Figure 2 is a perspective view of a section of the nacelle of Figure 1 along a longitudinal axis of the nacelle, the nacelle comprising a thrust reverser and a drive mechanism of the thrust reverser, said reverser having a movable cover movable between a closed and open position and a reversible flap movable between an open position and a closed position;
    Figures 3A, 3B, are top views of a section of the nacelle along a longitudinal axis of the nacelle and show a detail of the drive mechanism of the thrust reverser according to a first embodiment of the invention, during different stages of movement of the movable cover from its closed position (Figure 3A) to its open position (Figure 3B); and FIGS. 4A, 4B, 4C are views similar to FIG. 3 of the drive mechanism of the thrust reverser according to a second embodiment of the invention, during different stages of the movement of the movable cover from its closed position (Figure 4A) to an engagement position (Figure 4B) to its open position (Figure 4C).
    DETAILED DESCRIPTION OF THE EMBODIMENTS
    With reference to FIG. 1, an aircraft 10 comprises a fuselage 12 on each side of which a wing 14 is arranged under which is fixed, via a mast 16, at least one turbofan 100 according to the invention. The turbofan 100 has a nacelle 102, and from front to rear of the nacelle along the longitudinal axis X of the nacelle, a blower 102a and a motor 102b driving the blower 102a, both housed inside the basket 102.
    The turbofan 100 has a stream 202 between the nacelle 102 and the engine 20. In operation of the engine, a secondary air flow 208 (Figures 2) expelled by the blower circulates in the stream 202 to be expelled at the rear of the turbojet 100.
    With reference to FIGS. 2 and 3A-B, the nacelle 102 comprises, from front to rear along the longitudinal axis X of the nacelle, a fixed cover 206 fixedly mounted on the fixed structure of the nacelle 102 then at least one reverser thrust I can be activated / deactivated and having mobile parts, in particular at least one reversing flap 104 (only shown in FIG. 2) and a mobile cover 207.
    The fixed cover 206 and the mobile cover 207 have an external surface which constitutes the external envelope of the nacelle 102 and an internal surface which constitutes an external wall of the stream 202.
    The nacelle 102 also has, for each reversing flap 104, a through opening (or window) 210 through which the secondary stream communicates.
    202 and the exterior of nacelle 102.
    The movable cover 207 is mounted movable in translation, in a direction of translation generally parallel to the longitudinal axis X between a closed position in which it is brought closer to the fixed cover 206 and an open position in which it is distant from the cover fixed 206 so as to widen the opening 210. The translation is carried out by any suitable means such as for example slides where each slide is formed by a fitting 301 (not shown in FIG. 2) fixed on the movable cover 207 and sliding in a groove 302 (not shown in the figure
    2) arranged on the fixed structure of the nacelle 102.
    The fixed cover 206 delimits the opening 210 upstream relative to the longitudinal axis
    X while the movable cover 207, in the open position, delimits the opening 210 downstream relative to the longitudinal axis X.
    The reversing flap 104 is mounted so that it can rotate on the fixed structure of the nacelle 102 around an axis of rotation substantially perpendicular to the longitudinal axis X of the nacelle 102. The reversing flap 104 is movable between a closed position in which it closes the opening 210 and an open position in which it does not close the opening 210 and has a part extending through the vein 202 to deflect at least part of the secondary flow 208 towards the outside of the nacelle through opening 210.
    For example, as illustrated in FIG. 2, the reversing flap 104 has, in the open position, a part located outside of the nacelle 102.
    The reversing flap 104 is mechanically linked to the movable cover 207 so that the movement of the reversing flap 104 between its closed position and its open position is coordinated with the movement of the movable cover 207 between its closed position and its open position, and Conversely.
    This coordination is ensured by a drive mechanism 300, which with reference to FIG. 3, comprises in known manner:
    • at least one mechanical link (not shown) between the reversing flap 104 and the movable cover 207, for example a connecting rod articulated between the reversing flap 104 and the movable cover 207 • at least one actuator 304 (for example one on each side of the movable cover) fixed on the one hand to a fixed structure of the nacelle 102 and on the other hand to the fitting 301 of the movable cover, • a control unit (not shown), of the processor type, which controls the actuator (s) 304 to activate the thrust reverser I (from the closed / closed position to the open / open position), and vice versa, to deactivate the thrust reverser I (from the open / closed position) opening to the closed / closed position), as required by the aircraft 10.
    According to the invention, the drive mechanism 300 further comprises, for each actuator 304, an elastic means 320, constrained in compression or in traction, arranged between the movable cover 207 and the fixed structure of the nacelle 102 and having the purpose help the actuator 304 to oppose the forces induced by the aerodynamic pressures exerted on the components of the thrust reverser I.
    The elastic means 320 is fixed at a first end 321a to an anchoring point 325 secured to the fixed structure of the nacelle 102 and is fixed at a second end 321b to the fitting 301 of the movable cover 207,
    The elastic means 320 is, for example, a spring 321. In the example shown in FIG. 3, the spring 321 is a spiral spring which has its elongation axis disposed generally along an axis parallel to the longitudinal axis X of the nacelle 102. The anchoring point 325 is located in front of the fitting 301 along the longitudinal axis X of the nacelle.
    When the pilots of the aircraft wish to activate the thrust reverser I, the control unit pilots each actuator to produce, from the closed position of the reversing flap and the closing position of the movable hood (FIG. 3 A) , a first combination ensuring:
    a rearward translation (arrow 52 in FIG. 2) of the movable cover 207 which ensures the displacement of the movable cover 207 from the closed position to the open position, and
    - By the action of the mechanical link between the flap 104 and the movable cover 207, a rotation (arrow 54 in FIG. 2) of the reversing flap 104 around its axis of rotation which ensures the displacement of the reversing flap 104 from the closed position in the open position.
    During this first combination, the force required from each actuator 304 to initiate the rearward translational movement of the movable cover 207 is low compared to the capacity of the actuator 304 when the reversing flap 104 and the movable cover 207 are subjected to both a strong aerodynamic pressure which tends to move them, respectively, towards their open / open position. In this case, each actuator 304 is, during this first combination, controlled so as to control the activation speed of the thrust reverser (ie to slow down the movement of the movable hood 207, under the action aerodynamic pressure, to avoid damage to the thrust reverser). Each spring 321 associated with an actuator 304 is stretched during the translation of the movable cover 207 towards the rear, and tends to exert a force which opposes in proportion to the translational movement towards the rear of the movable cover 207 and thus comes to relieve the actuator 207 until the end of travel (FIG. 3B) of the translation of the movable cover 207 towards the rear.
    Conversely, when the pilots of the aircraft wish to deactivate the thrust reverser I, the control unit activates each actuator 304 in order to produce, from the open position of the reversing flap 104 and from the opening position of the movable cover 207 (FIG. 3B), a second combination ensuring:
    - a forward translation (arrow 56) of the movable cover 207 in the direction of translation which ensures the displacement of the movable cover 207 from the open position to the closed position, and
    - By the action of the mechanical link between the reversing flap 104 and the movable cover 207, a rotation (arrow 58) in the opposite direction of the reversing flap 104 around its axis of rotation which ensures the return of the reversing flap 104 from the open position in the closed position, and
    During this second combination, each actuator 304 pulls the movable cover 207 forward towards its closed position, with a resistive force during the translational travel of the movable cover 207. The force exerted by each actuator 304 must be sufficient to overcome the aerodynamic pressures exerted on the elements of the thrust reverser I.
    During the translation of the movable cover 207 forwards, the spring 321, which was tensioned during the first combination, applies a force which tends to bring the movable cover 207 towards the fixed cover 206 (FIG. 3A). The force that the actuator 304 must exert to bring the movable cover 207 back to the fixed cover 206 is therefore reduced by the value of the return force of the spring 321.
    Thanks to the invention, the capacity of each actuator 304 can be reduced since the drive mechanism 300, in particular the elastic means 320, brings an additional force intended to compensate for the use of an actuator of reduced dimensions. The actuator 304 having reduced dimensions has, during the few seconds of its operation, less power requirements. Thanks to the invention, it is therefore possible to find an actuator operating optimally, despite limitations of the available power of the aircraft, for deactivating the thrust reverser with a reduced deactivation time.
    Each actuator 304 is, for example, a hydraulic or pneumatic type actuator, the rod of which forms the movable part 304b articulated to the fitting 301 and the cylinder of which forms the body 304a fixed to the fixed structure of the nacelle or a screw system / nut (as sub-component of an electric jack) whose nut, or respectively the screw, forms the movable part 304b articulated to the fitting 301 and the screw, or respectively the nut, forms, by means of a electric motor or not, the body 304a fixed to the fixed structure of the nacelle.
    For example, by using a load spring of 5000N constrained in tension in a drive mechanism according to the invention, it is possible to reduce the dimensions of the cylinder by 15% (for cylinder values, without mechanism d drive according to the invention, with a stroke of 750 mm and with an outer cylinder casing of 5 mm). Thanks to this reduction in the dimensions of the jack, and for a maximum hydraulic fluid flow of 35 1 / min, the activation time of the thrust reverser goes from 2.5 to 1.1 seconds and the deactivation time goes from 7 to 2.4 seconds.
    As a variant (not shown), when the spring is constrained in compression, the anchoring point to which a first end of the spring is fixed is situated behind the fitting of the movable cover to which a second end of the spring is fixed. The movement of the fitting of the movable cover towards the anchoring point, when the movable cover is moved towards its open position, compresses the spring.
    In this case, during the first combination carried out by the control unit to activate the thrust reverser, each spring is compressed during the translation of the movable cover and tends to exert a force which is opposed in proportion to the translational movement towards the rear of the movable cover and relieves the jack until the end of its translation towards the rear.
    During the second combination performed by the control unit to deactivate the thrust reverser, the compressed spring applies a force which tends to bring the movable cover towards the fixed cover. The force of the jack necessary to bring the movable cover towards the fixed cover is therefore reduced by the value of the force exerted by the spring.
    In the embodiments described above, the elastic means 320 is engaged as soon as the actuator 304 is activated by the control unit.
    In another embodiment of the invention, the drive mechanism 300 comprises a delay mechanism 400 associated with the movable cover 207 and with the elastic means 320, so that at a predetermined position of the movable cover
    207, called engagement, when translating from the closed position to the open position of the movable cover, the elastic means 320 is engaged / engaged with the movable cover 207.
    Advantageously, the predetermined position is defined so that the elastic means 320 begins to be stretched / compressed for a stroke of the movable cover 207 close to 80% or even 90% of its maximum rearward stroke, that is to say when the forces required from the actuator 304 to brake the translation of the movable cover 207 are maximum. The delay mechanism thus makes it possible to use an elastic means 320 with a reduced stroke characteristic, and increased load.
    In an exemplary embodiment illustrated in FIGS. 4A-C in which the elastic means 320 is a spring 321 constrained in traction, the delay mechanism 400 comprises a free fitting 401 mounted movably in translation in the fitting 301 of the movable cover, and a stop 403 arranged on the fitting 301 of the movable cover and designed to drive the free fitting 401 with the fitting 301 of the movable cover (and thus tension the spring 321) when the movable cover 207 crosses the position of engagement during its movement towards the rear of nacelle 102.
    The spring 321 is fixed at a first end 321a to an anchor point 325 integral with the fixed structure of the nacelle 102 and at a second end 321b to the free fitting 401.
    The fitting is guided in a rail 402 arranged on the fitting 301 and extending along an axis parallel to the longitudinal axis X of the nacelle, and the stop 403 is arranged at the upstream end of the rail 402. The spring 321 is fixed at a first end 321a to an anchor point 325 secured to the fixed structure of the nacelle 102 and to a second end 321b to the free fitting 401. The anchor point 325 is located upstream of the free fitting 401 according to the longitudinal axis X of the nacelle.
    During the first combination performed by the control unit to activate the thrust reverser I, the fitting 301 of the movable cover 207 translates towards the rear of the nacelle, guided in the groove 302. The free fitting 401, retained by the spring 321 remains stationary until the movable cover 207 crosses the engagement position (FIG. 4B), beyond which the free fitting 401, retained by the spring 321, bears against the stop 403 .
    Beyond the engagement position, the movement of the fitting 301 of the movable cover 207 causes, via the stop 403, the movement of the free fitting 401 towards the rear and the tensioning of the spring 321 which then exerts a return force opposing the translational movement towards the rear of the movable cover 207. The return force relieves the actuator 304 until the end of travel (FIG. 4C) of the translation of the movable cover 207 towards the back.
    During the second combination carried out by the control unit to deactivate the thrust reverser I, the actuator 304 pulls (FIG. 4C) the movable cover 207 towards the front towards its closed position and the tensioned spring 321 exerts a restoring force on the movable cover 207, via the free fitting 401 bearing against the stop 403, causing the fitting 301 of the movable cover to move forward. The force ίο exerted by the spring 321 relieves the actuator 304 until the movable cover 207 crosses the engagement position (FIG. 4B) at which the spring 321 reaches its rest position and no longer exerts any force. on the free fitting 401. The free fitting 401 then stops relative to the fitting 301 of the movable cover which continues to translate forward until the movable cover 207 reaches its open position. From the maximum elongation position of the spring to the engagement position, that is to say when the forces required from the actuator 304 to pull the movable cover 207 forwards are maximum, the force required from the the actuator 304 for bringing the movable cover 207 towards the fixed cover 206 is therefore reduced by the value of the return force of the spring 321.
    In the following description, the invention is more particularly described for an inverter flap 104, but it is applied in the same way for each inverter flap 104 when there are several. In particular, there may be two reversing flaps 104 arranged one opposite the other, or four reversing flaps 104 distributed regularly over the periphery of the nacelle 102.
    In addition, the invention has been described for a reversing flap 104 intended to be partly projecting towards the outside of the nacelle 102 in the event of activation of the thrust reverser I and with a reversing flap 104 whose surface exterior of the shutter is in aerodynamic continuity of the outer surface of the fixed cover 206 and of the cover 207 when the reversing shutter is in the closed position.
    The invention could however be applied to any type of thrust reverser architecture, in particular of the type with reversing flap (also called door) hidden (that is to say housed in the movable cover 207 when the reverser thrust I is deactivated), or of type with double reversing flaps (also called double doors).
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1) Nacelle (102) for a turbofan (100), said nacelle (102) comprising:
    - A fixed structure carrying a fixed cover (206) and a mobile cover (207), the mobile cover (207) being movable in translation between a closed position in which the mobile cover is brought closer to the fixed cover (206) and a position opening in which the movable cover is remote from the fixed cover (206),
    - A through opening (210) delimited upstream by the fixed cover (206) and downstream by the movable cover (207) in its open position;
    - A reversing flap (104) mounted to rotate on the fixed structure of the nacelle around an axis of rotation, between a closed position in which said flap closes the opening (210) and an open position in which said flap n '' does not close the opening (210), and
    - A drive mechanism (300) of the reversing flap (104) and of the movable cover between said closed, closed and said open positions, of opening, respectively, reversing flap and movable cover, and vice versa, said mechanism drive (300) comprising at least one actuator (304) fixed on the one hand to the fixed structure of the nacelle (102) and on the other hand to a fitting (301) fixed to the movable cover, characterized in that the mechanism drive (300) further comprises, for each actuator (304), an elastic means (320) having a first end (321a) fixed to the fixed structure of the nacelle (102) and a second end fixed to the fitting ( 301).
    [2" id="c-fr-0002]
    2) nacelle (102) according to claim 1, characterized in that the drive mechanism (300) further comprises a delay mechanism (400) associated with the movable cover (207) and with the elastic means (320), so that at a predetermined position of the movable cover (207), called the engagement cover, when translating from the closed position to the open position of the movable cover, the elastic means (320) is engaged with the cover mobile (207).
    [3" id="c-fr-0003]
    3) nacelle (102) according to claim 2, characterized in that the delay mechanism (400) comprises a free fitting (401) mounted movable in translation in the fitting (301) of the movable cover, and a stop (403) arranged on the fitting of the movable cover (207).
    [4" id="c-fr-0004]
    4) nacelle (102) according to claim 3, characterized in that the free fitting (401) is mounted movable in translation in the fitting (301) of the movable cover by
    5 by means of a rail (402) extending along an axis parallel to the longitudinal axis (X) of the nacelle, and in that the stop (403) is arranged at one end of the rail (402).
    [5" id="c-fr-0005]
    5) Nacelle (102) according to any one of claims 1 to 4, characterized in that the elastic means (320) is constrained in traction.
    [6" id="c-fr-0006]
    6) Nacelle (102) according to any one of claims 1 to 4, characterized in 10 that the elastic means (320) is constrained in compression.
    [7" id="c-fr-0007]
    7) nacelle (102) according to any one of claims 1 to 6, characterized in that the elastic means (320) is a spring (321) having an elongation axis arranged parallel to the longitudinal axis (X) of Platform.
    [8" id="c-fr-0008]
    8) Nacelle (102) according to one of claims 1 to 7, characterized in that each actuator (304) is a hydraulic or pneumatic cylinder, or a screw nut system.
    3062
    3/6
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    类似技术:
    公开号 | 公开日 | 专利标题
    FR3062637A1|2018-08-10|TURBOREACTOR NACELLE HAVING A PUSH-INVERTER DRIVE MECHANISM
    EP0777045B1|2001-08-29|Thrust reverser with doors with linked rear panel
    CA2696712C|2014-10-28|Nacelle equipped with at least one excess pressure flap
    FR2952128A1|2011-05-06|THRUST INVERTER DEVICE
    EP0834651A1|1998-04-08|Method and device to close thrust reverser blocker doors
    FR2864021A1|2005-06-24|DEVICE FOR CONTROLLING THE MOTION OF A CLOSURE MEMBER FOR A VEHICLE
    FR2745036A1|1997-08-22|TURBOREACTOR THRUST INVERTER WITH DOORS ASSOCIATED WITH A UPSTREAM PANEL
    FR2959531A1|2011-11-04|DOOR INVERTER
    FR2982323A1|2013-05-10|PUSH REVERSING DEVICE
    CA2629055C|2016-08-23|Bypass turbofan engine comprising a thrust reverser
    CA2218449A1|1998-04-10|Thrust reverser with doors allowing controlled escape flow
    FR3057618A1|2018-04-20|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER
    EP0764779A1|1997-03-26|Thrust reverser with doors linked to a primary panel
    WO2011073558A1|2011-06-23|Reverse thrust device
    CA2204825C|2004-02-10|Jet turbine engine thrust reverser employing doors fitted with upstream panel
    WO2011117555A1|2011-09-29|Reverse thrust device
    EP0835999B1|2003-07-09|Thrust reverser with optimized actuator position
    FR2760788A1|1998-09-18|PUSH INVERTER WITH TURBO JET WITH PLATED EXTERNAL STRUCTURE
    FR2966882A1|2012-05-04|THRUST INVERTER FOR AIRCRAFT TURBOJET ENGINE WITH REDUCED ACTUATOR NUMBERS
    FR2920135A1|2009-02-27|Nacelle for dual-flow turbojet of airplane, has locking unit including elastic returning unit for longitudinally twisting arm with respect to cavity formed in rod when rod slides in envelope, such that rear returning of arm is prevented
    FR3064307A1|2018-09-28|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER
    EP3693593A1|2020-08-12|Turbojet comprising a mechanism for driving a thrust inverser
    FR2717859A1|1995-09-29|Double-flow turboshaft engine equipped with a thrust reversal system and a device for restricting the cold gas ejection channel, and restriction device fitted to such a turbine engine.
    EP3680177A1|2020-07-15|Turbojet nacelle comprising a reverser door and a system for assisting with the deployment of the reverser door
    EP3696396A1|2020-08-19|Active lock with levers for thrust reverser of an aircraft nacelle
    同族专利:
    公开号 | 公开日
    US10753314B2|2020-08-25|
    US20180230939A1|2018-08-16|
    CN108394564B|2021-05-04|
    CN108394564A|2018-08-14|
    FR3062637B1|2020-07-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4909442A|1984-05-14|1990-03-20|The Boeing Company|Actuation system for a blocker door in a jet engine nacelle|
    FR2929998A1|2008-04-14|2009-10-16|Aircelle Sa|DOUBLE FLOW TURBOREACTOR NACELLE|
    FR3006716A1|2013-06-10|2014-12-12|Aircelle Sa|THRUST INVERTER WITH THREADED JOINT LOCKING PAD THREE POINTS|
    WO2016059331A1|2014-10-13|2016-04-21|Snecma|Deployable grille with fins for aircraft turbine engine thrust-reversal system|
    EP3034848A1|2014-12-15|2016-06-22|United Technologies Corporation|Gas turbine engine and thrust reverser assembly therefor|WO2021023934A1|2019-08-05|2021-02-11|Safran Nacelles|Thrust reverser comprising at least one initiator to initiate the closing of a mobile external structure of this reverser|
    WO2021023935A1|2019-08-05|2021-02-11|Safran Nacelles|Aircraft thrust reverser comprising a braking mechanism for slowing a mobile cowl in the event of overtravel|US3814324A|1972-06-19|1974-06-04|Gen Electric|Propulsion nozzle and actuator system employed therein|
    US5309711A|1991-08-21|1994-05-10|Rohr, Inc.|Cascade type thrust reverser for fan jet engines|
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    FR2920131B1|2007-08-20|2010-01-08|Aircelle Sa|TURBOREACTOR NACELLE EQUIPPED WITH A SYSTEM FOR THE MECHANICAL INHIBITION OF A PUSH INVERTER|
    FR2984964B1|2011-12-23|2014-01-17|Aircelle Sa|DOOR FOR THRUST INVERTER WITH DOORS|
    US9016040B2|2012-11-30|2015-04-28|General Electric Company|Thrust reverser system with translating-rotating cascade and method of operation|
    US9976516B2|2014-03-21|2018-05-22|Rohr, Inc.|Thrust reverser for a turbofan engine|
    US10041443B2|2015-06-09|2018-08-07|The Boeing Company|Thrust reverser apparatus and method|FR3091691A1|2019-01-14|2020-07-17|Airbus Operations|NACELLE OF A TURBOREACTOR COMPRISING A REVERSE DOOR AND A DEVICE FOR ASSISTING THE DEPLOYMENT OF THE REVERSE DOOR|
    法律状态:
    2018-02-23| PLFP| Fee payment|Year of fee payment: 2 |
    2018-08-10| PLSC| Publication of the preliminary search report|Effective date: 20180810 |
    2020-02-19| PLFP| Fee payment|Year of fee payment: 4 |
    2021-02-24| PLFP| Fee payment|Year of fee payment: 5 |
    2022-02-16| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1751003|2017-02-07|
    FR1751003A|FR3062637B1|2017-02-07|2017-02-07|TURBOREACTOR NACELLE HAVING A DRIVE INVERTER DRIVE MECHANISM|FR1751003A| FR3062637B1|2017-02-07|2017-02-07|TURBOREACTOR NACELLE HAVING A DRIVE INVERTER DRIVE MECHANISM|
    CN201810112460.1A| CN108394564B|2017-02-07|2018-02-05|Nacelle for a turbofan engine|
    US15/889,778| US10753314B2|2017-02-07|2018-02-06|Turbojet engine nacelle comprising a thrust reverser drive mechanism|
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