• 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 double-flow turbojet (100) with a nacelle (102) comprising a slide (218) movable in translation between an advanced position and a retracted position to open a window between a vein and the outside, a plurality of blades (250), each being movable in rotation on the slider (218) between a retracted position and a deployed position, and a maneuvering system (400) moving each blade (250) and comprising for each blade (250), a shaft (402) movable in rotation on the slide (218) and on which the blade (250) is fixed, a toothed sector (406) fixed to the shaft ( 402), a toothed arc (408) movable in rotation on the slide (218), and having a bearing face, a threaded rod (510) fixedly mounted on the fixed structure (206), a cam (512) with a tapped hole screwed onto the threaded rod (510) and mounted fixed in translation with respect to the slider (218) and a return means (516) which forces the bearing face against the outer surface. The use of rotating blades on the slide and the simplified maneuvering system makes the assembly lighter than the use of state-of-the-art reversal doors. Fig. 5
    公开号:FR3098862A1
    申请号:FR1907966
    申请日:2019-07-15
    公开日:2021-01-22
    发明作者:Laurent Cazeaux；Antoine BOUDOU
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a bypass turbojet which comprises a series of blades which are rotatably mounted to close off the side flow stream, as well as to an aircraft comprising at least one such bypass turbojet.
    [0002] An aircraft has a fuselage on each side of which a wing is attached. Under each wing is suspended at least one double-flow turbojet. Each turbofan engine is fixed under the wing via a mast which is fixed between the wing structure and the structure of the turbofan.
    [0003] The bypass turbojet comprises an engine and a nacelle which is fixed around the engine. The double-flow turbojet engine has a secondary stream between the nacelle and the engine in which a secondary flow circulates.
    [0004] The nacelle comprises a plurality of reversing doors, each being movable in rotation on the structure of the nacelle between a retracted position in which it is outside the secondary vein and a deployed position in which it is positioned across the vein. secondary in order to divert the secondary flow to a window which is in the wall of the nacelle and which is open between the secondary vein and the exterior of the nacelle.
    [0005] Thus, the secondary flow is diverted to the outside and more precisely to the front of the turbojet engine in order to produce a counter thrust. In addition, the movement of each reversal gate is achieved with the aid of a connecting rod which passes through the secondary vein in the retracted position and which therefore partially obstructs the secondary vein.
    [0006] Although the reversing doors are entirely satisfactory, it is desirable to find different mechanisms, in particular mechanisms that are less heavy and which do not present any obstruction of the secondary flow in the retracted position.
    [0007] An object of the present invention is to provide a bypass turbojet which comprises a series of blades which are rotatably mounted to close off the stream of the secondary flow.
    [0008] To this end, a double-flow turbojet engine is proposed having a longitudinal axis and comprising an engine and a nacelle surrounding the engine which comprises a fan casing, where a vein of a secondary flow is delimited between the nacelle and the engine and in which an air flow circulates in a direction of flow, said nacelle comprising:
    [0009] - a fixed structure fixed to the fan casing,
    [0010] a movable assembly having a movable cover and a slide, the movable cover being fixed to the slide, the slide being movable in translation on the fixed structure in a direction of translation between an advanced position in which the slide is positioned so that the movable cowl is moved closer to the fan casing and a retracted position in which the slide is positioned so that the movable cowl is moved away from the fan casing to define between them an open window between the duct and the outside of the nacelle ,
    [0011] - a plurality of blades, each comprising a first end mounted so as to be able to rotate on the slide around an axis of rotation and where the blades are angularly offset step by step around the longitudinal axis, where each blade is movable between a retracted position in which the blade is outside the vein and a deployed position in which the blade is across the vein,
    [0012] - a set of actuators ensuring the movement of the slide between the advanced position and the retracted position, and vice versa, and
    [0013] - a maneuvering system intended to move each blade from the retracted position to the deployed position and vice versa, where the maneuvering system comprises:
    [0014] - for each blade, a shaft mounted to rotate on the slide around an axis of rotation, and on which the blade is fixed,
    [0015] - for each shaft, a toothed sector fixed to the shaft and coaxial with the axis of rotation,
    [0016] - a toothed arc coaxial with the longitudinal axis, mounted mobile in rotation on the slide around the longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, and where the toothed arc has a bearing face,
    [0017] - a threaded rod whose axis is parallel to the longitudinal axis and which is fixedly mounted on the fixed structure,
    [0018] - a cam having a threaded hole screwed onto the threaded rod and an outer face, where the cam is mounted fixed in translation with respect to the slide, and where the outer surface of the cam bears against the bearing face, and
    [0019] - a return means which forces the bearing face of the toothed arc against the outer surface of the cam.
    [0020] Such a turbojet enables mass reduction by replacing the reversing doors and their drive mechanisms with lighter pivoting blades with a simplified maneuvering system.
    [0021] Advantageously, the return means is a tension spring which is fixed between the toothed arc and the slide.
    [0022] Advantageously, the toothed arc is equipped with a roller which is mounted to rotate freely on the toothed arc about an axis parallel to the longitudinal axis and which is arranged so as to roll on the outer face of the cam when this one moves in rotation.
    [0023] According to a particular embodiment, the bypass turbojet comprises an upstream support and a downstream support which are integral with the slide, and the upstream support is in flat support against a front face of the cam and the downstream support is in flat support. against a rear face of the cam.
    [0024] According to another particular embodiment, the bypass turbojet comprises an upstream ball thrust bearing which bears flat against a front face of the cam and a downstream thrust bearing which bears flat against a rear face of the cam, each Ball stopper is integral with the slide, and each ball stopper is threaded onto the threaded rod.
    [0025] The invention also proposes an aircraft comprising at least one bypass turbojet according to one of the preceding variants.
    [0026] The characteristics of the invention mentioned above, as well as others, will emerge more clearly on reading the following description of an exemplary embodiment, said description being given in relation to the accompanying drawings, among which:
    [0027] is a side view of an aircraft comprising a bypass turbojet according to the invention,
    [0028] is a perspective view of the bypass turbojet according to the invention in the forward and retracted position,
    [0029] is a perspective view of the bypass turbojet according to the invention, in the retracted and deployed position,
    [0030] is a schematic representation of a bypass turbojet according to the invention seen in section through a vertical plane,
    [0031] is a perspective view of a maneuvering system according to the invention, and
    [0032] is a perspective view of a locking system according to a particular embodiment.
    [0033] DETAILED EXPOSURE OF EMBODIMENTS
    [0034] 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.
    [0035] 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 engine 100 according to the invention. The bypass turbojet 100 is attached to the wing 14 by means of a mast 16.
    [0036] Fig. 2 and FIG. 3 show the bypass turbojet 100 which has a nacelle 102 and an engine 20 which is housed inside the nacelle 102 and which comprises a fan housing 202. The engine 20 is represented by its rear ejection part.
    [0037] In the description which follows, and by convention, the longitudinal axis of the turbofan engine 100 which is parallel to the longitudinal axis of the aircraft 10 oriented positively towards the front of the aircraft 10 is called X, the term Y is called Y the transverse axis which is horizontal when the aircraft is on the ground, and Z the vertical axis, these three directions X, Y and Z being orthogonal to each other.
    [0038] Fig. 2 and FIG. 3 show the bypass turbojet 100 in two different positions of use and FIG. 4 shows a schematic sectional representation of the bypass turbojet 100.
    [0039] The bypass turbojet 100 has between the nacelle 102 and the engine 20, a duct 204 in which circulates a secondary flow 208 coming from the air inlet through a fan 300 and which therefore flows in the direction of flow. that goes from front to back.
    [0040] The nacelle 102 has a fixed structure 206 which is fixedly mounted on the fan casing 202. The fixed structure 206 is composed in particular here of a front frame 210 mounted around the fan casing 202 and of outer panels 212 forming an aerodynamic surface. which are shown in transparency in FIG. 3 and a part of which is cut out in FIGS. 2 and 3.
    [0041] The nacelle 102 has a movable assembly 214 which has a movable cowl 216 (also transparent in Fig. 3) a part of which is cut out in Figs. 2 and 3 and which forms the outer walls of the nozzle.
    [0042] The nacelle 102 also has a slide 218. The slide 218 here takes the form of a cylinder with perforated walls. The movable cowl 216 is attached to and downstream of the slider 218 relative to the direction of the air flow in the turbofan 100.
    [0043] The slide 218 is mounted to move in translation in a direction of translation generally parallel to the longitudinal axis X on the fixed structure 206 of the nacelle 102.
    [0044] The slider 218 is movable between an advanced position (Fig. 2) and a retracted position (Fig. 3) and vice versa. In the forward position, the slider 218 is positioned as far forward as possible with respect to the direction of flow so that the movable cowl 216 is brought closer to the outer panels 212 and the fan housing 202 and thus forms an aerodynamic surface. In the retracted position, the slider 218 is positioned as far back as possible with respect to the direction of flow so that the movable cowl 216 is away from the outer panels 212 and from the fan casing 202 so as to define a window between them. 220.
    [0045] In the advanced position, the movable cowl 216 and the exterior panels 212 extend so as to define the exterior surface of the nacelle 102, and the movable cowl 216 and the fan housing 202 extend so as to define the exterior surface of the duct. 204.
    [0046] In the retracted position, the movable cowl 216 and the fan casing 202 as well as the exterior panels 212 are at a distance and between them define the window 220 open between the vein 204 and the exterior of the nacelle 102. That is, say that the air from the secondary flow 208 passes through the window 220 to reach the outside of the bypass turbojet 100.
    [0047] The translation of the slide 218 is carried out by any suitable means, such as, for example, slide systems between the fixed structure 206 and the slide 218.
    [0048] The nacelle 102 also includes a set of actuators (not shown) ensuring the translational movement of the slide 218 between the advanced position and the retracted position and vice versa. Each actuator is controlled by a control unit, for example of the processor type, which controls movements in one direction or the other according to the needs of the aircraft 10.
    [0049] Each actuator can take, for example, the form of a double-acting cylinder (two working directions), the cylinder of which is fixed to the fixed structure 206 and a rod fixed to the slide 218.
    [0050] In order to direct the flow of air coming out of the window 220, cascades can be attached to the slider 218 opposite the window 220.
    [0051] Fan housing 202 and exterior panels 212 define window 220 upstream from the direction of flow and movable cowl 216 defines window 220 downstream from direction of flow.
    [0052] The nacelle 102 comprises a plurality of blades 250, each being mounted so as to be able to rotate on the slide 218 about an axis of rotation which is here generally parallel to the longitudinal axis X. Each blade 250 is thus movable between a retracted position ( Fig. 2) in which the blade 250 is outside the vein 204 and an extended position (Fig. 3) in which the blade 250 is across the vein 204 in order to divert the secondary flow 208 towards the window 220.
    [0053] Each blade 250 is movably mounted at a first end while a second end approaches the motor 20 when the blade 250 is deployed in order to close the vein 204 as well as possible.
    [0054] The blades 250 are angularly offset step by step around the longitudinal axis X.
    [0055] The number of blades 250 as well as the shape of each of them depend on the dimensions of the double-flow turbojet engine 100 as well as on the width of each blade 250 so that, in the deployed position, the blades 250 block most of the vein 204. .
    [0056] The passage from the retracted position to the deployed position is effected by a rotation of the blade 250 towards the interior of the turbojet 100.
    [0057] The retracted position can be adopted when the slider 218 is in the forward position or in the retracted position. The deployed position can only be adopted when the slider 218 is in the retracted position.
    [0058] The slide 218 also carries an operating system 400 which moves each blade 250 from the retracted position to the deployed position and vice versa.
    [0059] The operation thus consists, from the advanced / retracted position, in controlling the activation of the actuators to move the slide 218 from the advanced position to the retracted position. During this movement, the maneuvering system 400 moves the blades 250 from the retracted position to the deployed position.
    [0060] Conversely, the operation thus consists, from the retracted / deployed position, of controlling the activation of the actuators to move the slider 218 from the retracted position to the advanced position. During this movement, the maneuvering system 400 moves the blades 250 from the deployed position to the retracted position.
    [0061] The use of the blades 250 rotatably mounted on the slider 218 allows a lightening of the assembly compared to the use of reversal doors of the state of the art.
    [0062] Fig. 5 shows the operating system 400 on the mobile assembly 214 and more particularly on the slide 218 which is seen here in transparency in phantom.
    [0063] For each blade 250, the operating system 400 comprises a shaft 402 which is mounted so as to be able to rotate on the slide 218 about an axis of rotation 404, and on which the blade 250 is fixed. In Fig. 5, each blade 250 is truncated to facilitate understanding of the mechanism and only two blades 250 are shown. The axis of rotation 404 is here generally parallel to the longitudinal axis X.
    [0064] For each shaft 402, the operating system 400 also includes a toothed sector 406 fixed to the shaft 402 and coaxial with the axis of rotation 404.
    [0065] The maneuvering system 400 also includes a toothed arc 408, the axis of which is coaxial with the longitudinal axis X. The toothed arc 408 is rotatably mounted on the movable assembly 214 and more particularly on the slide 218 around the longitudinal axis X. In the embodiment of the invention presented in FIG. 5, the toothed arc 408 comprises a support plate 409 which here generally takes the form of a crown and, for each toothed sector 406, a toothed sub-arc 407 fixed to the support plate 409, but it is also possible to provide a toothed arc which extends over all the toothed sectors 406.
    [0066] The attachment of each toothed sub-arch 407 to the support plate 409 is effected, for example, by screwing systems.
    [0067] The teeth of the toothed arc 408, here of each toothed sub-arc 407, mesh with the teeth of each toothed sector 406. Thus, a rotational movement of the toothed arc 408 causes the rotation of each toothed sector 406 and therefore of the associated blade 250.
    [0068] Each blade 250 extends in a plane generally perpendicular to the longitudinal axis X.
    [0069] The operating system 400 also includes a threaded rod 510 whose axis is parallel to the longitudinal axis X and which is fixedly mounted on the fixed structure 206.
    [0070] The operating system 400 also includes a cam 512 having a threaded hole screwed onto the threaded rod 510 and an outer face eccentric with respect to the axis of the threaded hole.
    [0071] The cam 512 is also mounted fixed in translation with respect to the slide 218, that is to say that a translation of the slide 218 causes the same translation of the cam 512. In the embodiment of the invention presented in Fig. 5, the cam 512 is caught between two supports 514a-b integral with the slide 218, where an upstream support 514a is in flat support against a front face of the cam 512 and where a downstream support 514b is in flat support against a rear face of cam 512. Of course, any other translation locking system is possible.
    [0072] The common thread between the threaded rod 510 and the tapped hole is large enough for the translational movement of the cam 512 to cause it to rotate, for example the 1000 mm thread.
    [0073] Thus, when the slider 218 moves in translation, the cam 512 moves in the same way and because of its engagement with the threaded rod 510, it rotates around the axis of its tapped hole and the threaded rod 510.
    [0074] The outer surface of the cam 512 bears against a bearing face of the toothed arc 408 and more particularly here of the support plate 409.
    [0075] The maneuvering system 400 also includes a return means 516 which forces the bearing face of the toothed arc 408 against the outer surface of the cam 512. In the embodiment of the invention shown in FIG. 5, the return means 516 is a tension spring which is fixed between the toothed arc 408 and more particularly here of the support plate 409, and part of the slide 218. Of course, any other return means is possible as per example a compression spring by providing a suitable assembly.
    [0076] Thus, when the rotation of the cam 512 tends to push back the support plate 409, the latter rotates around the longitudinal axis X, causing in rotation each toothed sub-arc 407 and therefore each toothed sector 406 and thus each blade 250 d 'a first position to a second position.
    [0077] Conversely, in the case of the reverse rotation of the cam 512, the latter does not push back the support plate 409 which returns to its first position under the effect of the return means 516.
    [0078] In the embodiment of the invention presented here, the first position is the retracted position as shown in Fig. 5 and the second position is the deployed position which is reached after a rotation shown by arrow 520, but a reverse arrangement is also possible.
    [0079] The movement of all the blades 250 is then relatively simple to implement and it does not require actuators other than those necessary for the movement of the slide 218.
    [0080] In order to facilitate the sliding of the outer face of the cam 512 against the bearing face of the toothed arc 408, the latter is equipped with a roller 518 (seen in dotted lines) which is mounted to rotate freely on the toothed arc 408 around an axis parallel to the longitudinal axis X and which is arranged so as to roll on the outer face of the cam 512 when the latter moves in rotation.
    [0081] In the embodiment of the invention shown in FIG. 5, the slider 218 comprises a U-section 219 coaxial with the longitudinal axis X and open towards the longitudinal axis X. The U-section 219 forms a cage inside which the toothed arc 408 is mounted to be movable in rotation. around the longitudinal axis X and where the shafts 402 are mounted to be movable in rotation through the walls of the U-profile 219 around the axis of rotation 404.
    [0082] The rotational guidance of the toothed arc 408 relative to the U-profile 219 is provided by any appropriate means such as for example a system of grooves and studs sliding in the groove.
    [0083] Fig. 6 shows another embodiment of the system for locking in translation of the cam 512. In this embodiment, the locking system comprises two thrust ball bearings 614a-b which are integral with the slide 218 and which are mounted here fixed to the interior of U-profile 219 which is shown in transparency in phantom. The use of thrust ball bearings limits friction.
    [0084] Each thrust ball bearing 614a-b is threaded onto the threaded rod 510 and there is an upstream ball thrust bearing 614a which bears flat against a front face of the cam 512 and a downstream thrust bearing 614b which bears flat against a rear face of the cam 512.
    [0085] 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)
    [0001]
    Turbofan engine (100) having a longitudinal axis (X) and comprising an engine (20) and a nacelle (102) surrounding the engine (20) which comprises a fan casing (202), where a vein (204) of a secondary flow (208) is delimited between the nacelle (102) and the engine (20) and in which an air flow circulates according to a direction of flow, said nacelle (102) comprising: - a fixed structure (206) fixed to the fan casing (202), - a movable assembly (214) having a movable cowl (216) and a slider (218), the movable cowl (216) being fixed to the slider (218), the slider (218) being movable in translation on the fixed structure (206 ) in a direction of translation between an advanced position in which the slider (218) is positioned so that the movable cowl (216) is brought closer to the fan casing (202) and a retracted position in which the slider (218) is positioned so that the movable cowl (216) is away from the fan casing (202) to define between them a window (220) open between the vein (204) and the outside of the nacelle (102), - a plurality of blades (250), each comprising a first end mounted so as to be able to rotate on the slider (218) around an axis of rotation and where the blades (250) are angularly offset step by step around the axis longitudinal (X), where each blade (250) is movable between a retracted position in which the blade (250) is outside the vein (204) and a deployed position in which the blade (250) is across the vein (204), - a set of actuators ensuring the movement of the slider (218) between the advanced position and the retracted position, and vice versa, and - an operating system (400) intended to move each slat (250) from the retracted position to the deployed position and vice versa, where the operating system (400) comprises: - for each blade (250), a shaft (402) rotatably mounted on the slider (218) around an axis of rotation (404), and on which the blade (250) is fixed, - for each shaft (402), a toothed sector (406) fixed to the shaft (402) and coaxial with the axis of rotation (404), - a toothed arc (408) coaxial with the longitudinal axis (X), rotatably mounted on the slider (218) around the longitudinal axis (X), where the teeth of the toothed arc (408) mesh with the teeth of each toothed sector (406), and where the toothed arc (408) has a bearing face, - a threaded rod (510) whose axis is parallel to the longitudinal axis (X) and which is mounted fixed on the fixed structure (206), - a cam (512) having a threaded hole screwed onto the threaded rod (510) and an outer face, where the cam (512) is mounted fixed in translation relative to the slider (218), and where the outer surface of the cam (512) bears against the bearing face, and - a return means (516) which constrains the bearing surface of the toothed arc (408) against the outer surface of the cam (512).
    [0002]
    Turbofan engine (100) according to Claim 1, characterized in that the return means (516) is a tension spring which is fixed between the toothed arc (408) and the slider (218).
    [0003]
    Turbofan engine (100) according to one of Claims 1 or 2, characterized in that the toothed arc (408) is equipped with a roller (518) which is mounted to rotate freely on the toothed arc (408) around an axis parallel to the longitudinal axis (X) and which is arranged so as to roll on the outer face of the cam (512) when the latter moves in rotation.
    [0004]
    Turbofan engine (100) according to one of Claims 1 to 3, characterized in that it comprises an upstream support (514a) and a downstream support (514b) which are integral with the slider (218), and in that the the upstream support (514a) is flat against a front face of the cam (512) and the downstream support (514b) is flat against a rear face of the cam (512).
    [0005]
    Turbofan engine (100) according to one of Claims 1 to 3, characterized in that it comprises an upstream ball thrust bearing (614a) which bears flat against a front face of the cam (512) and a thrust bearing downstream balls (614b) which bears flat against a rear face of the cam (512), in that each ball bearing (614a-b) is integral with the slider (218), and in that each ball bearing ( 614a-b) is threaded onto the threaded rod (510).
    [0006]
    Aircraft (10) comprising at least one turbofan engine (100) according to one of the preceding claims.
    类似技术:
    公开号 | 公开日 | 专利标题
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    FR3107317A1|2021-08-20|DOUBLE-FLOW TURBOREACTOR WITH MOBILE DEFLECTORS AND A SCREW ACTUATOR
    FR3094757A1|2020-10-09|TURBOREACTOR CONTAINING A NACELLE EQUIPPED WITH AN INVERTER SYSTEM AND A MOBILE CASCADES GRID
    FR3074852A1|2019-06-14|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER FLAP AND A DEVIATION GRID FOR FORMING AN INVERSION FLOW
    FR3066232A1|2018-11-16|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER
    同族专利:
    公开号 | 公开日
    US20210017935A1|2021-01-21|
    FR3098862B1|2021-07-16|
    US11187190B2|2021-11-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2933890A|1955-01-20|1960-04-26|Boeing Co|Nozzle closing jet deflectors|
    US20170198658A1|2016-01-11|2017-07-13|The Boeing Company|Thrust reverser|
    FR3059646A1|2016-12-07|2018-06-08|Safran Nacelles|NACELLE FOR AIRCRAFT TURBOREACTOR EQUIPPED WITH A DEVICE FOR DETECTING DEFORMATION OF ITS MOBILE STRUCTURE|
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    US10018151B2|2015-01-14|2018-07-10|The Boeing Company|Methods and apparatus to vary reverse thrust of aircraft engines|
    FR3078999A1|2018-03-13|2019-09-20|Airbus Operations|DOUBLE FLOW TURBOREACTOR COMPRISING A SERIES OF ROTATING BLADES TO SHUT THE VEIN FROM THE SECONDARY FLOW|
    FR3092145A1|2019-01-24|2020-07-31|Airbus Operations|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES TO CLOSE THE SECONDARY FLOW VEIN|FR3090048A1|2018-12-13|2020-06-19|Airbus Operations|DOUBLE FLOW TURBOREACTOR COMPRISING A SERIES OF ROTATING BLADES FOR SEALING THE SECONDARY FLOW Vein|
    FR3092145A1|2019-01-24|2020-07-31|Airbus Operations|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES TO CLOSE THE SECONDARY FLOW VEIN|
    FR3094412A1|2019-03-25|2020-10-02|Airbus Operations|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES TO CLOSE THE SECONDARY FLOW VEIN|
    法律状态:
    2020-07-22| PLFP| Fee payment|Year of fee payment: 2 |
    2021-01-22| PLSC| Publication of the preliminary search report|Effective date: 20210122 |
    2021-07-28| PLFP| Fee payment|Year of fee payment: 3 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1907966|2019-07-15|
    FR1907966A|FR3098862B1|2019-07-15|2019-07-15|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES TO CLOSE THE SECONDARY FLOW VEIN|FR1907966A| FR3098862B1|2019-07-15|2019-07-15|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES TO CLOSE THE SECONDARY FLOW VEIN|
    US16/926,973| US11187190B2|2019-07-15|2020-07-13|Turbofan comprising a cam actuating a set of rotatable blades for blocking off the bypass flow duct|
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