• 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) carrying cascades and movable in translation. between an advanced 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 flaps (104), each hingedly mounted on the main slider (207b) between a closed position in which it closes the window (210) and an open position in which it is closed. not 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) passing each reversing shutter (104) from the closed position in the open position when the secondary slide (214) passes 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:FR3064308A1
    申请号:FR1752385
    申请日:2017-03-23
    公开日:2018-09-28
    发明作者:Frederic RIDRAY；Lionel Czapla；Frederic Piard
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    (57) The invention relates to a turbojet engine (100) comprising an engine (20) with a fan casing (206a) and a nacelle (102) comprising a movable cover (207a) and a main slide (207b) carrying cascades and movable in translation between an advanced position and a retracted position in which the movable cover (207a) and the fan casing (206a) define between them a window (210). The nacelle (102) also comprises a plurality of reversing flaps (104), each one being articulated on the main slide (207b) between a closed position in which it closes the window (210) and an open position in which it does not close not 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) passing each reversing flap (104) from the closed position in the open position when the secondary slide (214) passes from the first position to the second position, and a set of actuators ensuring a displacement in translation of the main slide (207b) and the secondary slide (214).

    i
    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 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 secondary flow air 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 comprises a nacelle equipped with a plurality of reversing flaps with a different opening mechanism.
    To this end, a dual-flow turbojet engine is proposed 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, said nacelle comprising:
    - a fixed structure attached to the fan casing,
    a mobile assembly having a mobile cover and a main slide carrying cascades, the mobile cover being fixed to and downstream of the main slide, 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 moved away from the fan casing to define between them a open window between a stream of a secondary flow and the outside of the nacelle through one of the waterfalls and,
    - a plurality of reversing flaps, each one being articulated on the main slide between a closed position in which it closes an area of the window and an open position in which it does not close said area of the window,
    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 transmission system provided for passing each reversing flap from the closed position to the open position when the secondary slide passes from the first position to the second position and vice versa,
    a set of actuators designed to ensure, from the advanced and closed position, 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 Conversely.
    Such a turbojet engine makes it possible, among other things, to reduce the number of actuators used to actuate the reversing flaps.
    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.
    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 open position, FIG. 5 is a perspective view of a section of the reactor in the advanced position, FIG. 6 is a perspective view identical to that of FIG. 5 in the retracted and closed position, FIG. 7 is a perspective view identical to that of FIG. 5 in the retracted and open position, FIG. 8 shows a sectional view along the plane VIII of FIG. 4, FIG. 9 shows a sectional view along the plane 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 an aircraft in the advancing position as shown in FIG. 1.
    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 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.
    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.
    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 6 o'clock beam 206e, the 9 o'clock beam 206d and the 12 o'clock 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, the 9 o'clock beam 206d and the 12 o'clock beam 206c.
    The cross member 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 which integrates cascades 209 allowing the redirection of the flow passing from the interior to the exterior. The main slide 207b here takes the form of a cylinder with perforated walls. The movable cover 207a is fixed to and downstream from the main slide 207b.
    In the embodiment of the invention presented here, the cascades 209 cover the perforated walls of the main slide 207b and the cascades 209 are not shown in Figs. 5 to 7 to allow viewing of the mechanisms described below. Of course, it is also possible to plan that the waterfalls will be absent.
    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 translation of the main slide 207b is achieved by systems of slides between the 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 9 o'clock and 6 o'clock slide links. 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 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 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 vein 202 and the outside of the nacelle 102 through one of the cascades 209 of the main slide 207b. That is, the air from the secondary flow 208 passes through the window 210 by passing through one of the cascades 209 of the main slide 207b to reach the outside of the double-flow turbojet 100.
    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 window 210 is located opposite a cascade 209 of the main slide 207b.
    The nacelle 102 comprises a plurality of 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 is mounted articulated on the main slide 207b between a closed position (Figs. 2, 3, 5 and 6) and an open position (Figs. 4 and 7) and vice versa.
    The closed position can be adopted when the main slide 207b is in the advanced position or in the retracted position. The open position can only be adopted when the main slide 207b is in the retracted position.
    In the closed 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 open 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.
    Thus, in the closed position, each reversing flap 104 is generally in the extension of the movable cover 207a and in the open position, each reversing flap 207b is positioned across the vein 202 and deflects at least part of the secondary flow 208 towards the outside. through window 210.
    In the advanced position, each reversing flap 104 is positioned outside the fan casing 206a.
    Each reversing flap 104 is articulated at 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 the closed position and towards the motor 20 in the open 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 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. There are therefore a secondary slide 214 for several reversing flaps 104.
    The transmission system 216 is provided for passing each reversing flap 104 from the closed position to the open position when the secondary slide 214 passes from the first position to the second position 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 open of the reversing flaps 104 therefore consists, from the advanced and closed position, in moving the main slide 207b by translation relative to the frame 206b for reaching the retracted and closed position, moving the secondary slide 214 from the first position to the second position to cause the reversing flaps 104 to pass from the closed position to the open 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 and closed position, a translational movement of the main slide
    207b 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 may for example take the form of a double-acting telescopic rod cylinder. There are thus several jacks each cylinder of which is fixed to the 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 each second rods is fixed to the secondary slide 214.
    Each actuator 218, 220 can take the form of a double-acting cylinder, for example. There are thus first jacks 218, each having a cylinder fixed to the 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 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 for each half of the nacelle 102 and for moving 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 movement 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 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.
    ίο
    权利要求:
    Claims (4)
    [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), 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) carrying waterfalls (209), the movable cover (207a) being fixed to and downstream of the main slide (207b), the main slide (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 fan casing (206a) and a retracted position in which the main slide (207b) is positioned so that the movable cover (207a) is remote from the fan casing (206a) to define between them a window (210) open between a vein (202) of a secondary flow (208) and the exterior of the nacelle (102) through one of the waterfalls (209) and,
    - A plurality of reversing flaps (104), each being hinged mounted on the main slide (207b) between a closed position in which it closes an area of the window (210) and an open position in which it does not close said area window (210),
    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 transmission system (216) provided for passing each reversing flap (104) from the closed position to the open position when the secondary slide (214) passes from the first position to the second position and vice versa,
    a set of actuators (218, 220) intended to ensure, from the advanced and closed position, a translational movement of the main slide (207b) to the retracted position, then the translational movement of the 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 in the retracted position, the main slide (207b) is pressurized against the fixed structure (206) of the nacelle (102).
    [3" id="c-fr-0003]
    3) turbofan engine (100) according to claim 2, characterized in that 5 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 fan casing (206a) has a stop (224) against which the stop (222) abuts in the retracted position.
    [4" id="c-fr-0004]
    4) Aircraft (10) comprising at least one turbofan engine (100) according to one of claims 1 to 3.
    1/4
    206a
    206b
    218
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    同族专利:
    公开号 | 公开日
    US20180274484A1|2018-09-27|
    US10690088B2|2020-06-23|
    FR3064308B1|2021-06-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2946094A1|2009-06-02|2010-12-03|Aircelle Sa|THRUST INVERTER FOR DOUBLE FLOW TURBOREACTOR NACELLE.|
    WO2013021136A1|2011-08-08|2013-02-14|Snecma|Thrust reverser device for compact jet pipe|
    EP3034848A1|2014-12-15|2016-06-22|United Technologies Corporation|Gas turbine engine and thrust reverser assembly therefor|
    EP3103995A2|2015-06-09|2016-12-14|The Boeing Company|Thrust reverser apparatus and method|FR3091855A1|2019-01-22|2020-07-24|Airbus Operations|NACELLE OF A TURBOREACTOR CONTAINING A mobile assembly AND A reinforced fixed structure|US3815357A|1971-01-28|1974-06-11|Rohr Industries Inc|Thrust reversing apparatus|
    US3829020A|1973-06-13|1974-08-13|Boeing Co|Translating sleeve variable area nozzle and thrust reverser|
    FR2935444B1|2008-09-02|2010-09-10|Airbus France|THRUST INVERTER AND NACELLE FOR AN AIRCRAFT PROVIDED WITH AT LEAST ONE SUCH INVERTER|
    FR2949141B1|2009-08-14|2011-07-15|Aircelle Sa|PUSH REVERSING DEVICE|
    US9784214B2|2014-11-06|2017-10-10|Rohr, Inc.|Thrust reverser with hidden linkage blocker doors|
    EP3103956B1|2015-06-12|2021-02-17|Ewald Holler|Modular supporting profile with rod recesses|
    US10077740B2|2015-10-16|2018-09-18|The Boeing Company|Folding door thrust reversers for aircraft engines|
    FR3067760B1|2017-06-14|2019-06-28|Airbus Operations|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS|FR3067760B1|2017-06-14|2019-06-28|Airbus Operations|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS|
    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|
    US10906661B2|2018-11-05|2021-02-02|Rohr, Inc.|Nacelle cowl hinge|
    法律状态:
    2018-03-23| PLFP| Fee payment|Year of fee payment: 2 |
    2018-09-28| PLSC| Publication of the preliminary search report|Effective date: 20180928 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 4 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1752385A|FR3064308B1|2017-03-23|2017-03-23|TURBOREACTOR CONTAINING A NACELLE EQUIPPED WITH INVERTER FLAPS|
    FR1752385|2017-03-23|FR1752385A| FR3064308B1|2017-03-23|2017-03-23|TURBOREACTOR CONTAINING A NACELLE EQUIPPED WITH INVERTER FLAPS|
    US15/926,757| US10690088B2|2017-03-23|2018-03-20|Jet engine comprising a nacelle equipped with reverser flaps|
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