• 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 motor (20) with a fan casing (206a) and a nacelle (102) comprising a movable hood (207a) and a main slide (207b) and movable in translation between a position and a retracted position in which the movable cowl (207a) and the fan case (206a) define between them a window (210). The nacelle (102) also comprises a plurality of reversing (104) and external (105) shutters, each being articulated on the main slide (207b) between a stored position in which it closes the window (210) and a deployed position in it does not close the window (210), a secondary slide (214) movable in translation on the main slide (207b) between a first and a second position, a transmission system (216, 217) passing each reversing shutter (104) and outside (105) from the stored position to the extended position when the secondary slide (214) moves from the first position to the second position, and a set of actuators providing translational movement of the main slide (207b) and the secondary slide (214).
    公开号:FR3067760A1
    申请号:FR1755332
    申请日:2017-06-14
    公开日:2018-12-21
    发明作者: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 dual-flow turbojet engine which comprises a nacelle equipped with a plurality of reversing flaps, as well as to an aircraft comprising at least one such dual-flow turbojet 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 double-flow turbojet engine is fixed under the wing by means of a mast which is fixed between the structure of the wing and the structure of the double-flow turbojet engine.
    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 in rotation on the structure of the nacelle between a stored position in which it comes in continuity with the external surface of the nacelle and a deployed position in which it opens a window in the wall of the nacelle to expel the air from the secondary flow towards the outside of the nacelle. Generally, we find housed in the window, a grid ("cascade" in Anglo-Saxon terminology) which allows to straighten the secondary air flow towards the front of the nacelle in order to produce a counter-thrust.
    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 comprises a nacelle equipped with a plurality of 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, where a stream of a secondary flow is delimited between the nacelle and the engine and in which an air flow flows in a direction of flow, said nacelle comprising:
    - a fixed structure attached to the fan casing,
    a movable assembly having a movable cover and a main slide, the movable cover being fixed to and downstream of the main slide relative to the direction of flow, the main slide being movable in translation on the fixed structure in a direction of translation between an advanced position in which the main slide is positioned so that the movable cover is brought closer to the fan casing and a retracted position in which the main slide is positioned so that the movable cover is distant from the fan casing for define between them an open window between the vein and the outside of the nacelle,
    a plurality of reversing flaps arranged inside the nacelle, each being mounted articulated by a downstream edge, with respect to the direction of flow, on the main slide between a stored position in which it closes an area of the window and a deployed position in which it does not close said zone of the window and extends towards the motor,
    - A plurality of external flaps which are arranged outside the nacelle, where each external flap is mounted articulated by a downstream edge, relative to the direction of flow, on the main 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 and extends towards the outside of the nacelle,
    a secondary slide mounted movable in translation parallel to the direction of translation on the main slide between a first position and a second position,
    a first transmission system provided for passing each reversing flap from the stored position to the deployed position simultaneously with the passage of the secondary slide from the first position to the second position and vice versa,
    a second transmission system provided for passing each external flap from the stored position to the deployed position simultaneously with the passage of the secondary slide from the first position to the second position and vice versa, and
    - A set of actuators provided to ensure, from the advanced position of the main slide, a translational movement of the main slide to the retracted position, then the translational movement of the secondary slide from the first position to the second position and vice versa.
    Such a turbojet engine makes it possible, among other things, to reduce the number of actuators used to actuate the reversing flaps. In addition, such a turbojet engine does not include elements such as grids to straighten the air flow passing through the secondary vein towards the front of the nacelle. Indeed, the air flow is straightened forward only by the reversing and external flaps in the deployed position.
    Advantageously, each external flap is mounted opposite a reversing flap.
    Advantageously, in the retracted position, the main slide is forced into pressure against the fixed structure of the nacelle.
    Advantageously, the main slide has stops distributed angularly around the periphery of the main slide, and for each stop, the fan casing has a stop against which the stop comes into abutment in the retracted position.
    Advantageously, the main slide has stops distributed angularly around the periphery of the main slide, and for each stop, a front frame of the fixed structure has a stop against which the stop comes into abutment in the retracted position.
    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, FIG. 3 is a perspective view of a section of a nacelle according to the invention in the advanced position, FIG. 4 is a perspective view identical to that of FIG. 3 in the retracted and deployed position, FIG. 5 is a perspective view of a section of the turbojet engine in the advanced position, FIG. 6 is a perspective view identical to that of FIG. 5 in the retracted and stored position, FIG. 7 is a sectional view of the turbojet engine in the retracted and deployed position, FIG. 8 shows a sectional view along the plane VIII of FIG. 4, FIG. 9 shows a sectional view along line IX-IX of FIG. 7, and FIG. 10 shows a view similar to that of FIG. 9 for a particular embodiment.
    DETAILED DESCRIPTION OF EMBODIMENTS
    In the following description, the terms relating to a position are taken with reference to the direction of air flow in a turbojet engine which therefore flows from the front to the rear 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 the turbofan 100 which has a nacelle 102 and a motor 20 which is housed inside the nacelle 102 and which comprises a fan casing 206a. The motor 20 is embodied here by its front cone and its blower 22 inside the air inlet of the nacelle 102.
    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 towards the front 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 l 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.
    Fig. 3 and FIG. 4 show part of the nacelle 102 and FIGS. 5 to 7 show part of the turbofan 100.
    As shown in Figs. 5 to 7, the turbofan 100 has between the nacelle 102 and the engine 20, a vein 202 in which circulates the secondary flow 208 coming from the air inlet through the blower 22 and which therefore flows according to the direction of flow from upstream to downstream.
    The nacelle 102 has a fixed structure 206 which is fixedly mounted on the fan casing 206a. The fixed structure 206 is composed of a front frame 206b mounted around the fan casing 206a. The front frame 206b is connected to the fan casing 206a via the 6hour beam 206e, the 3hour9hour 206h beam 206d and the 12hour beam 206c. The front frame 206b as well as the beams 6hour 206e, 9hour 206d and 12hour 206c can be an integral part of the fixed structure 206 of the nacelle 102.
    The fixed structure 206 of the nacelle 102 is intended to be fixed only to the fan casing 206a. More specifically, the nacelle 102 is fixed to the fan casing 206a by means of the 6 o'clock beams 206e, of the 3 o'clock 9 o'clock beam 206d and of the 12 o'clock beam 206c.
    The cross 231 located at 12 o'clock makes it possible to connect the left fixed structure to the right fixed structure at 12 o'clock, more particularly the left beam 12 o'clock 206c to the right beam 12 o'clock 206c.
    It is also possible to add one or more displacement limiters 231a in connection with the mast 16, constituting a Y stop with a certain clearance corresponding to the displacement to be tolerated.
    The nacelle 102 has a movable assembly 207 which has a movable cover
    207a forming the walls of the nozzle and a main slide 207b. The main slide 207b here takes the form of a cylinder with perforated walls. The movable cover 207a is fixed to and downstream of the main slide 207b relative to the direction of flow.
    The main slide 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 o'clock beam 206c and the 6 o'clock beam 206e.
    The main slide 207b is translated by slide systems between the front frame 206b and the main slide 207b.
    Fig. 8 shows an example of a particular embodiment of the system of slides between the 12 o'clock beam 206c and the main slide 207b. This embodiment is applicable to the 3 o'clock-9 o'clock and 6 o'clock slide connections. In this embodiment, the main slide 207b has a rib 802 in the form of a straight rod, and the 12-hour beam 206c has a groove 804 of a shape adapted to allow the rib 802 to slide.
    The main slide 207b is movable between an advanced position (Figs. 2, 3 and 5) and a retracted position (Figs. 4, 6 and 7) and vice versa. In the advanced position, the main slide 207b is positioned as far forward as possible relative to the direction of flow so that the movable cover 207a is brought closer to the fan casing 206a. In the retracted position, the main slide 207b is positioned as far back as possible relative to the direction of flow so that the movable cover 207a is distant from 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 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 stream 202 and the outside of the nacelle 102. That is to say that the air coming from of the secondary flow 208 passes through the window 210 to reach the outside of the double-flow turbojet 100 and is oriented towards the front of the nacelle 102 using the external flaps 105 making it possible to produce a counter-thrust.
    The fan casing 206a delimits the window 210 upstream relative to the longitudinal axis X and the movable cover 207a delimits the window 210 downstream relative to the longitudinal axis X.
    The nacelle 102 comprises a plurality of reversing flaps 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 reversing flap 104 is mounted articulated on the main slide 207b between a stored position (Figs. 2, 3, 5 and 6) and a deployed position (Figs. 4 and 7) and vice versa. The passage from the stored position to the deployed position is effected by a rotation of the reversing flap 104 towards the inside of the turbojet 100.
    The stored position can be adopted when the main slide 207b is in the advanced position or in the retracted position. The deployed position can only be adopted when the main slide 207b is in the retracted position.
    In the stored position, each reversing flap 104 closes an area of the openwork part of the main slide 207b when the latter is in the advanced position and the same area of the openwork part of the main slide 207b and a window area 210 when the main slide 207b is in the back position. In the deployed position, the reversing flap 104 does not close said zone of the window 210 or the perforated part of the main slide 207b allowing the passage of the secondary flow 208 and the reversing flap 104 extends towards the motor 20.
    Thus, in the stored position, each reversing flap 104 is generally in the extension of the movable cover 207a and in the deployed position, each reversing flap 104 is positioned across the stream 202 and deflects at least part of the secondary flow 208 outward. through the window 210, the flow is oriented towards the front using the external flaps 105.
    In the advanced position, each reversing flap 104 is positioned outside the fan casing 206a.
    Each reversing flap 104 is articulated by a downstream edge, relative to the flow direction, to the downstream part of the main slide 207b on hinges 212 fixed to the main slide 207b while the opposite free edge is positioned upstream in position stored and towards the motor 20 in the deployed position.
    The nacelle 102 comprises a plurality of external flaps 105 which are shown in transparency in FIGS. 5 and 6. The external flaps 105 are distributed over the periphery and outside of the nacelle 102 as a function of the angular opening of the window 210 around the longitudinal axis X. The external flaps 105 are arranged at the exterior with respect to the reversing flaps 104. According to a particular embodiment, each exterior flap 105 is mounted opposite a reversing flap 104.
    Each external flap 105 is mounted articulated on the main slide 207b between a stored position (Figs. 2, 3, 5 and 6) and a deployed position (Figs. 4 and 7) and vice versa. The transition from the stored position to the deployed position is effected by a rotation of the external flap 105 towards the outside of the turbojet 100. The articulations of the external flaps 105 are generally opposite the articulations of the reversing flaps 104 thus as shown on Fig. 7, when the reversing flaps 104 and the external flaps 105 are deployed, they generally form a continuity.
    The stored position can be adopted when the main slide 207b is in the advanced position or in the retracted position. The deployed position can only be adopted when the main slide 207b is in the retracted position. The deployed position, respectively stored, of the external flaps 105 is synchronized with the deployed position, respectively stored, of the reversing flaps 104.
    In the stored position, each external flap 105 closes an area of the openwork part of the main slide 207b when the latter is in the advanced position and the same area of the openwork part of the main slide 207b and a window area 210 when the main slide 207b is in the back position. In the deployed position, the external flap 105 does not close said zone of the window 210 nor the perforated part of the main slide 207b and extends towards the outside of the nacelle 102 allowing the passage of the secondary flow 208.
    Thus, in the stored position, each external flap 105 is generally in the extension of the movable cover 207a and in the deployed position, each external flap 105 opens outwards and deflects the part of the secondary flow 208 which has been previously deflected by the reversing flaps 104 through window 210.
    In the advanced position, each external flap 105 is positioned outside the reversing flaps 104.
    Each outer flap 105 is articulated by a downstream edge, relative to the direction of flow, to the downstream part of the main slide 207b on hinges 213 fixed to the main slide 207b while the opposite free edge is positioned upstream in position stored and outward in the deployed position.
    The mobile assembly 207 also has a secondary slide 214 which is mounted mobile in translation in a direction parallel to the direction of translation on the main slide 207b. The secondary slide 214 is thus movable between a first position and a second position.
    The mobile assembly 207 also has a first transmission system 216 which, for each reversing flap 104, here takes the form of a rod articulated by one end to the reversing flap 104 and articulated by another end to the secondary slide 214.
    Similarly, the mobile assembly 207 also has a second transmission system 217 which, for each external flap 105, here takes the form of a rod articulated by one end to the external flap 105 and articulated by another end to the slide. secondary 214.
    There is therefore a secondary slide 214 for several reversing flaps 104 and external flaps 105.
    The first transmission system 216 is provided for passing each reversing flap 104 from the stored position to the deployed position simultaneously with the passage of the secondary slide 214 from the first position to the second position in order to uncover the reversing flaps 104 and vice versa.
    The second transmission system 217 is provided for passing each external flap 105 from the stored position to the deployed position simultaneously with the passage of the secondary slide 214 from the first position to the second position in order to uncover the external flaps 105 and vice versa.
    In the embodiment of the invention presented here, the first position consists in moving the secondary slider 214 forwards while the second position consists in moving the secondary slider 214 backwards.
    The translation of the secondary slide 214 is carried out by systems of slides between the main slide 207b and the secondary slide 214 which can take, for example, the same shape as that described in FIG. 8. The secondary slide 214 is guided radially by means of rollers or skids.
    Fig. 9 shows an example of a particular embodiment of the guide of the secondary slide 214. The main slide 207b here has U-shaped profiles 225 which extend parallel to the longitudinal axis X and which are open towards the inside and the secondary slide 214 has a yoke 227 which extends radially in one of the U-shaped profiles 225 and which carries pads or rollers 902 between said yoke 227 and each of the sides of the U-shaped profile 225.
    Fig. 10 shows an example of a particular embodiment of the guide of the secondary slide 214. The main slide 207b here has U-shaped profiles 225 which extend parallel to the longitudinal axis X and which are open towards the outside and the secondary slider 214 has two axis + roller assemblies 904 on either side of the main slider 207b and fixed to the secondary slider 214. The U-shaped profile 225 (which may have a different shape, for example in I or T) carries pads 908 to take up the radial forces of the secondary slide 214 and the rails 906 allowing the recovery of the forces perpendicular to the radial forces of the secondary slide 214. The combination of the rails 906 and the rollers 904 makes it possible to guide the secondary slide 214 during its translation along the longitudinal axis X.
    The transition from the advanced position of the main slide 207b to the retracted position of the main slide 207b and deployed of the reversing flaps 104 and of the external flaps 105 therefore consists, from the advanced position of the main slide 207b and therefore of the stored positions of the reversing flaps 104 and outside
    105, to move back the main slide 207b by translation relative to the front frame 206b to reach the retracted position for the main slide 207b and the stored positions of the reversing flaps 104 and outside 105, to move the secondary slide 214 from the first position to the second position for passing the reversing flaps 104 and the external flaps 105 from the stored position to the deployed position.
    Reverse movement returns to the advanced position.
    The nacelle 102 also comprises a set of actuators 218 and 220 ensuring the displacement in translation of the main slide 207b and the secondary slide 214. Each actuator 218, 220 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.
    The set of actuators 218, 220 is thus provided to ensure, from the advanced position of the main slide 207b and therefore from the stored positions of the reversing flaps 104 and outside 105, a movement in translation of the main slide 207b up to the retracted position, then the translational movement of the secondary slide 214 from the first position to the second position and vice versa. During the movement of the main slide 207b, the secondary slide 214 which is carried by the main slide 207b follows the same movement.
    Each actuator 218, 220 can take the form, for example, of a double-acting telescopic rod cylinder (two working directions). There are thus several jacks each cylinder of which is fixed to the front frame 206b and more generally to the fixed structure 206 of the nacelle 102, and the end of each of the first rods of which is fixed to the main slide 207b and the end of which each of the second rods is fixed to the secondary slide 214.
    Each actuator 218, 220 can take, for example, the form of a double-acting cylinder (two working directions). There are thus first jacks 218, each having a cylinder fixed to the front frame 206b and more generally to the fixed structure 206 of the nacelle 102, and a rod fixed to the main slide 207b. There are thus second cylinders 220, each having a cylinder fixed to the main slide 207b and a rod fixed to the secondary slide 214.
    Each actuator 218, 220 may for example take the form of a motor meshing with a rack. There are thus first motors, each being fixed to the front frame 206b and meshing with a rack fixed to the main slide 207b. There are thus second motors, each being fixed to the main slide 207b and meshing with a rack fixed to the secondary slide 214.
    In the embodiment presented here, there are three actuators 218 for each half of the nacelle 102 and for moving the main slide 207b and three actuators 220 (only two are seen in Fig. 4) for each half of the nacelle 102 and to move the secondary slide 214.
    The number of actuators 218, 220 is therefore reduced compared to the number of actuators of the state of the art, hence a saving in weight.
    So that any possible deformation of the main slider 207b is avoided during the displacement of the secondary slider 214, the main slider 207b is forced under pressure against the fixed structure 206 of the nacelle 102 in the retracted position. To this end, the actuators 218 which move the main slide 207b move it until it is in abutment against the fixed structure 206 of the nacelle 102 and hold it thus until the return to the advanced position is not request. Such an abutment makes it possible to temporarily fix the main slide 207b.
    In the embodiment of the invention presented here, the main slide 207b has stops 222 distributed angularly around the periphery of the main slide 207b, and for each stop 222, the fan casing 206a or the front frame 206b of the fixed structure 206 has, for each stop 222, a stop 224 against which the stop 222 abuts in the retracted position.
    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 (6)
    [1" id="c-fr-0001]
    1) Double-flow turbojet engine (100) comprising an engine (20) and a nacelle (102) surrounding the engine (20) which comprises a fan casing (206a), where a stream (202) of a secondary flow (208) is delimited between the nacelle (102) and the motor (20) 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),
    - A movable assembly (207) having a movable cover (207a) and a main slide (207b), the movable cover (207a) being fixed to and downstream of the main slide (207b) relative to the direction of flow, the slide main (207b) being movable in translation on the fixed structure (206) in a direction of translation between an advanced position in which the main slide (207b) is positioned so that the movable cover (207a) is brought closer to the casing blower (206a) and a retracted position in which the main slide (207b) is positioned so that the movable cover (207a) is remote from the blower housing (206a) to define between them a window (210) open between the vein (202) and the exterior of the nacelle (102),
    - A plurality of reversing flaps (104) arranged inside the nacelle (102), each being mounted articulated by a downstream edge, relative to the direction of flow, on the main slide (207b) between a position stored 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) and extends towards the motor (20),
    - A plurality of external flaps (105) which are arranged outside the nacelle (102), where each external flap (105) is mounted articulated by a downstream edge, relative to the direction of flow, on the main slide (207b) 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) and extends towards the outside of the nacelle ( 102)
    a secondary slide (214) mounted movable in translation parallel to the direction of translation on the main slide (207b) between a first position and a second position,
    a first transmission system (216) provided for passing each reversing flap (104) from the stored position to the deployed position simultaneously with the passage of the secondary slide (214) from the first position to the second position and vice versa,
    - a second transmission system (217) provided for passing each external flap (105) from the stored position to the deployed position simultaneously with
    5 passage of the secondary slide (214) from the first position to the second position and vice versa, and
    - A set of actuators (218, 220) provided to ensure, from the advanced position of the main slide, a translational movement of the main slide (207b) to the retracted position, then the translational movement of the
    10 secondary slide (214) from the first position to the second position and vice versa.
    [2" id="c-fr-0002]
    2) Double-flow turbojet engine (100) according to claim 1, characterized in that each external flap (105) is mounted opposite a reversing flap (104).
    [3" id="c-fr-0003]
    3) turbofan engine (100) according to one of claims 1 or 2, 15 characterized in that in the retracted position, the main slide (207b) is constrained in pressure against the fixed structure (206) of the nacelle (102 ).
    [4" id="c-fr-0004]
    4) turbofan (100) according to claim 3, characterized in that the main slide (207b) has stops (222) angularly distributed around the periphery of the main slide (207b), and in that for each stop (222 ), the
    20 fan casing (206a) has a stop (224) against which the stop (222) abuts in the retracted position.
    [5" id="c-fr-0005]
    5) turbofan (100) according to claim 3, characterized in that the main slide (207b) has stops (222) angularly distributed around the periphery of the main slide (207b), and in that for each stop (222 ), a
    25 front frame (206b) of the fixed structure (206) has a stop (224) against which the stop (222) abuts in the retracted position.
    [6" id="c-fr-0006]
    6) Aircraft (10) comprising at least one turbofan engine (100) according to one of claims 1 to 5.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3067760B1|2019-06-28|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS
    EP1239139B1|2005-12-14|Thrust reverser actuating system in a turbojet engine
    EP0301939A1|1989-02-01|Turbine thrust reverser having a mobile deflector
    EP0365425A1|1990-04-25|Thrust reverser with balanced pivotable doors
    FR3064308A1|2018-09-28|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS
    CA2763523A1|2010-12-09|Thrust reverser for a dual-flow turbine engine nacelle
    EP0882881B1|2003-07-30|Doors with optimally deployable spoilers for a jet engine thrust reverser
    EP3530925B1|2020-12-16|Turbine engine comprising a nacelle provided with a reverser system comprising outer and inner doors
    EP0806563A1|1997-11-12|Doors with deflector vanes for a thrust reverser of a turbofan engine
    EP0692619A1|1996-01-17|Double flux turbine thrust reverser with external blocker flaps
    EP3415749B1|2021-05-05|Nacelle with thrust reverser system creating limited aerodynamic disturbances
    EP3421771A1|2019-01-02|Turbojet engine comprising a nacelle with thrust reverser flaps
    EP0654598B1|1998-08-26|Thrust reverser for a turbofan engine
    EP0807752B1|2003-08-13|Thrust reverser of the pivoting door type with a moveable liner pannel
    CA2152883C|2004-01-13|Turbofan thrust reverser, with obstructions linked to the primary enclosure
    EP3550134A1|2019-10-09|Turbine engine comprising a nacelle provided with a reverser system comprising a hinged cover
    FR3074854A1|2019-06-14|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH AN INVERTER SYSTEM COMPRISING DOORS
    FR3082889A1|2019-12-27|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH REVERSING SHUTTERS PROVIDED WITH MEANS FOR GENERATING VORTS
    EP3521604B1|2020-12-23|Turbine engine comprising a nacelle provided with a reverser system comprising doors
    EP3719293B1|2022-01-19|Turbojet engine comprising a nacelle provided with an inverser system and a mobile cascade grid
    EP3643909A1|2020-04-29|Turbojet engine comprising a nacelle provided with a translatably mobile thrust reverser system and a fan housing provided with supports
    EP3327274B1|2019-12-04|Turbojet nacelle comprising an inverser flap and an additional flap
    FR3074852A1|2019-06-14|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER FLAP AND A DEVIATION GRID FOR FORMING AN INVERSION FLOW
    FR3057617A1|2018-04-20|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER
    同族专利:
    公开号 | 公开日
    US20180372025A1|2018-12-27|
    US10995700B2|2021-05-04|
    FR3067760B1|2019-06-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3815357A|1971-01-28|1974-06-11|Rohr Industries Inc|Thrust reversing apparatus|
    FR2935444A1|2008-09-02|2010-03-05|Airbus France|Thrust reverser for bypass nacelle of airplane, has displacement units arranged with respect to internal and external doors such that displacement units are received in housing formed in cowl, when doors are in inactive position|
    EP3103995A2|2015-06-09|2016-12-14|The Boeing Company|Thrust reverser apparatus and method|
    EP3165752A2|2015-10-16|2017-05-10|The Boeing Company|Folding door thrust reversers for aircraft engines|EP3715613A1|2019-03-25|2020-09-30|Airbus Operations|Dual-flow turbojet engine comprising a series of rotary strips for blocking the secondary flow stream|US3829020A|1973-06-13|1974-08-13|Boeing Co|Translating sleeve variable area nozzle and thrust reverser|
    WO2004046533A2|2002-10-11|2004-06-03|The Nordam Group, Inc.|Bifold door thrust reverser|
    FR2946094B1|2009-06-02|2014-04-18|Aircelle Sa|THRUST INVERTER FOR DOUBLE FLOW TURBOREACTOR NACELLE.|
    FR2949141B1|2009-08-14|2011-07-15|Aircelle Sa|PUSH REVERSING DEVICE|
    FR2978991A1|2011-08-08|2013-02-15|Snecma|THRUST INVERSION DEVICE FOR COMPACT PIPE|
    US9784214B2|2014-11-06|2017-10-10|Rohr, Inc.|Thrust reverser with hidden linkage blocker doors|
    EP3034848B1|2014-12-15|2018-08-29|United Technologies Corporation|Gas turbine engine and thrust reverser assembly therefor|
    US10030608B2|2015-05-15|2018-07-24|Rohr Inc.|Variable area fan nozzle actuation system|
    EP3103956B1|2015-06-12|2021-02-17|Ewald Holler|Modular supporting profile with rod recesses|
    US9915226B2|2015-06-18|2018-03-13|Rohr, Inc.|Variable area fan nozzle hidden blocker door thrust reverser|
    FR3064308B1|2017-03-23|2021-06-11|Airbus Operations Sas|TURBOREACTOR CONTAINING A NACELLE EQUIPPED WITH INVERTER FLAPS|EP3184436A1|2015-12-23|2017-06-28|Airbus Operations, S.L.|Door system for an exhaust gas duct of an auxiliary power unit of an aircraft|
    FR3064308B1|2017-03-23|2021-06-11|Airbus Operations Sas|TURBOREACTOR CONTAINING A NACELLE EQUIPPED WITH INVERTER FLAPS|
    FR3087498B1|2018-10-22|2021-03-05|Airbus Operations Sas|TURBOREACTOR CONTAINING A NACELLE EQUIPPED WITH A MOBILE THRUST INVERSION SYSTEM IN TRANSLATION AND A BLOWER HOUSING EQUIPPED WITH SUPPORTS|
    法律状态:
    2018-12-21| PLSC| Search report ready|Effective date: 20181221 |
    2020-06-19| PLFP| Fee payment|Year of fee payment: 4 |
    2021-06-22| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1755332A|FR3067760B1|2017-06-14|2017-06-14|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS|
    FR1755332|2017-06-14|FR1755332A| FR3067760B1|2017-06-14|2017-06-14|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS|
    US16/007,761| US10995700B2|2017-06-14|2018-06-13|Jet engine comprising a nacelle equipped with reverser flaps|
    [返回顶部]