• 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:
    To reduce aerodynamic disturbances in a secondary channel of an aircraft turbomachine, the invention provides a thrust reverser system (40) comprising a thrust reversal gate (46) and an inverter gate (50) housed in a thrust space. housing (60) located outside a secondary channel (24), the system also comprising connecting pieces (52a, 52b) whose presence combined with the action of the jack (42) simultaneously produce: - a rearwards movement of the gate (46) towards a nacelle opening (70), released by a nacelle cowling (28) driven rearwards with the grid; and - a combined movement of the inverter door (50) relative to the gate (46) leading to the displacement of the front end of the door rearwards along the gate, and to the pivoting of this gate so as to cause the diving from its rear end into the secondary channel (24).
    公开号:FR3067406A1
    申请号:FR1755315
    申请日:2017-06-13
    公开日:2018-12-14
    发明作者:Olivier Pautis
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    The invention relates to the field of thrust reverser systems for aircraft turbomachines.
    More specifically, it relates to systems comprising thrust reversal grids, fitted to turbofans with double flow.
    The invention also relates to an aircraft comprising turbomachines equipped with such thrust reverser systems. It applies preferentially to commercial aircraft.
    STATE OF THE PRIOR ART
    Thrust reversal systems are for example known from documents FR 2 935 444 and FR 2 935 354. Among the different principles of thrust reversal implemented on aircraft turbomachines, there are known grate systems d 'inversion, provided with passages oriented so as to redirect forward the air from the secondary channel, to generate the counter-thrust force. Air is forced out of this secondary channel by inverter doors at least partially closing this channel, in the active configuration of the system.
    On the other hand, in the inactive configuration, each inverter door is in the retracted position in which it participates in the formation of the external wall of the secondary channel, also called OFS (from the English "Outer Fixed Structure"). More specifically, in this inactive configuration of the inverter system, each door reconstitutes a part of this external wall of the secondary channel, within an external movable cowling of the nacelle enclosing the inversion grid. During the transition from the inactive configuration to the active configuration, the external mobile cowling is moved rearward by jacks so as to release the grid, and to bring the inverter doors to their position for closing the secondary channel, via appropriate mechanical kinematics.
    This principle, although widespread, nevertheless suffers from a problem of aerodynamic disturbances of the air flow passing through the secondary channel in the inactive configuration of the system. In fact, in this configuration, the air flow within the secondary channel is disturbed during its passage over the junction zones between the body of the external movable cowling, and the inverter doors attached to this body. This results in drag as well as pressure losses within the secondary channel, which lead to a decrease in the overall performance of the turbomachine.
    There is therefore a need to optimize the design of these thrust reverser systems, in order to reduce the disturbances of the air flow in the secondary channel, in the inactive configuration of the thrust reverser system.
    STATEMENT OF THE INVENTION
    To respond at least partially to this need, the subject of the invention is a thrust reverser system for a turbomachine of an aircraft with double flow, the reverser system comprising at least one thrust reversing grid through which is intended to circulate the air of a secondary channel of the turbomachine in active configuration of the inverter system, the latter also comprising at least one inverter door configured to at least partially close said secondary channel when the system is in active configuration, the system also comprising at least one actuating cylinder.
    According to the invention, in an inactive configuration of the reverser system, the door is housed in a housing space located outside said secondary channel and in which is also located said grid driven by said cylinder and of which a rear end is integral with '' an external mobile nacelle cowling, the system also comprising:
    - A first connecting piece, a first end of which is connected to the inside of said external mobile nacelle cowling by a first articulated connection, and a second end of which is connected to the reverser door by a second articulated connection;
    - A second connecting part, a first end of which is connected to a rear end of the inverter door by a third articulated connection, and a second end of which is connected to an interior wall of the secondary channel by a fourth articulated connection.
    In addition, the inverter door is mounted at its front end on the grid by a fifth link allowing this front end to slide along the grid and to pivot relative to the latter, the second articulated link being arranged between the third articulated link and the fifth link so that during a transition from the inactive configuration to the active configuration, the action of said jack simultaneously produces:
    - a rearward movement of the grid in the direction of a nacelle opening, released by the external mobile nacelle cowling driven rearward with the grid; and
    - A combined movement of the inverter door relative to the grid leading on the one hand to the displacement of the front end of the door towards the rear along the grid, and on the other hand to the pivoting of this door according to the fifth connection so as to cause the plunging of its rear end into the secondary channel.
    The invention thus contrasts with the conventional embodiments of grid inverter systems, by providing an inverter door arranged outside the secondary channel in the inactive configuration of the system, and which moves relative to the grid while plunging into the channel secondary when switching to the active configuration. Thanks to this design specific to the present invention, when the system is in the inactive configuration, the inverter door no longer disturbs the air flow passing through the secondary channel of the turbomachine. Advantageously, this improves the overall performance of the turbomachine.
    The invention preferably provides at least one of the following optional characteristics, taken individually or in combination.
    In the inactive configuration, the first connecting piece is housed in the housing space located outside said secondary channel while remaining inside a fixed external cover of the nacelle, and the second connecting piece is housed in part in this housing space.
    In the inactive configuration, part of the second connecting part is arranged substantially radially in the secondary channel, and preferably intended to be masked from a secondary air flow by an arm of an intermediate casing of the turbomachine, also known as OGV (from the English “Outlet Guide Vane”), and in active configuration, said second connecting piece is arranged locally substantially parallel to the inner wall of the secondary channel.
    The first connecting piece preferably adopts an overall shape of an L.
    The cylinder comprises a cylinder rod articulated on a front end of the grid.
    The fifth link comprises at least one door guide rail integral with the grid and extending along the latter, as well as a roller cooperating with this rail and mounted on the front end of the inverter door.
    Said accommodation space is an interior space of the nacelle.
    In the inactive configuration, the grid and the inverter door are substantially parallel and are each located at least in part radially opposite a fan casing of the turbomachine.
    The system comprises several adjacent grids in the tangential direction of the turbomachine, preferably so as to form a set of grids extending over an angular sector of 300 to 360 ° around a longitudinal axis of the turbomachine, and each grid is associated with an inverter door.
    The grids are mechanically connected to each other so that the number of cylinders is preferably less than the number of grids. However, these two numbers could be identical, without departing from the scope of the invention.
    The invention also relates to a turbomachine of an aircraft with double flow comprising a thrust reverser system such as that described above, as well as an aircraft comprising at least one such turbomachine.
    Other advantages and characteristics of the invention will appear in the detailed non-limiting description below.
    BRIEF DESCRIPTION OF THE DRAWINGS
    This description will be made with reference to the accompanying drawings, among which;
    - Figure 1 shows a side plan view of an aircraft comprising a turbomachine equipped with a thrust reverser system according to the invention;
    - Figure 2 shows a partial view in longitudinal section of the turbomachine shown in the previous figure, with its thrust reverser system in the inactive configuration;
    - Figure 3 shows a partial perspective view of the turbomachine shown in the previous figure;
    - Figure 4 shows a cross-sectional view of the turbomachine shown in Figures 2 and 3 (without the OGV);
    - Figure 5 shows a view similar to that of Figure 2, during a transition from an inactive configuration to an active configuration of the thrust reverser system; and
    - Figures 6 to 8 show views similar to those of Figures 2 to 4, with the thrust reverser system being in the active configuration.
    DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
    Referring to Figure 1, there is shown an aircraft 100 of the commercial aircraft type, comprising two wings 2 (only one visible in Figure 1) attached to a fuselage 3 and each carrying a turbomachine 1 of the double-flow type, such as 'a turbojet engine.
    A preferred embodiment of the turbomachine 1 will now be described with reference to FIGS. 2 to 4. Throughout the following description, by convention, the direction X corresponds to the longitudinal direction of the turbomachine, this direction being parallel to the longitudinal axis 6 of this turbomachine. On the other hand, the direction Y corresponds to the direction oriented transversely with respect to the turbomachine, and the direction Z corresponds to the vertical or height direction, these three directions X, Y, Z being orthogonal to each other.
    Conventionally, the turbomachine 1 comprises a fan casing 8 centered on the axis 6 and extended by an intermediate casing 10, formed by a hub 12 and an outer shroud 14 connected to this hub by means of arms 16 shown diagrammatically in FIG. 4. The arms 16 extend substantially radially, and constitute at least for some of them outlet guide vanes, also called OGV (from the English “Outlet Guide Vane”). Preferably, at least some of these arms 16 are structural in addition to being aerodynamically profiled. The hub 12 is extended towards the rear by a central casing also called core casing, referenced 18 in FIG. 4 and enclosing the heart of the turbomachine. Around the central casing, there is an inter-vein compartment 20 delimited by a fixed internal cover 22, also called IFS. More precisely, it is an inner wall 22 delimiting a secondary annular channel 24 of the turbomachine. This channel 24 is delimited at the front by the fan casing 8 as well as by the intermediate casing, then extends towards the rear, therefore being delimited internally by the cowling 22, and externally by an external wall of the secondary channel 26, also known as OFS. The latter is integrated into an external movable cowling of the nacelle 28. In fact, the turbomachine 1 also includes a nacelle 30, a front part of which is produced by hollow cowls 32 surrounding the fan casing 8 and the outer shell 14 of the casing intermediate. These covers 32 are generally called fan covers. They are mounted articulated so as to allow access to operators, for carrying out maintenance operations. The covers 32 are extended towards the rear by the aforementioned external mobile cowling 28, the latter being able in fact to be translated towards the rear relative to the nacelle covers 32, along the longitudinal axis 6. In this regard, it is mentioned that throughout the description, the terms “front” and “rear” are considered with respect to the direction of advance of the aircraft following the thrust of its turbomachines, this direction of advance being represented by arrow 34 in the figure 2.
    In this environment, there is integrated a thrust reverser system 40 specific to the present invention, and an embodiment of which will now be described in its inactive configuration, as shown in FIGS. 2 to 4.
    First of all, it is noted that the reverser system 40 is produced from several modules which are repeated and which are arranged adjacent in the tangential direction of the turbomachine, all around the axis 6. As this will be detailed below, each module comprises a thrust reversing grid 46 and an inverter door 50. At least some of these modules each comprise, in the front part, a jack 42 whose body is for example fixedly mounted on the fan casing 8. The jack 42 comprises a jack rod 43 which is articulated on a front end of the thrust reversing grid 46.
    In the inactive configuration, the grid 46 is located radially outward, facing the fan casing 8 and the outer shell 14 of the intermediate casing. The grid 46 is located in front of the external movable cowling 28, and the rear end of this grid 46 is integral with the front end of the cowling 28. Consequently, during the movements observed during the actuation of the system thrust reverser 40, the grid 46 and the cowling 28 form a single, integral assembly which undergoes the same axial displacements.
    In the inactive configuration, the grid 46 and the actuator rod 43 are therefore in an advanced position of the nacelle, at the level of the fan cowls, which have a diameter usually greater than that of the tapered rear part of the nacelle. , which allows more space for their integration. This advantageously results in a nacelle 30 of reduced outside diameter. In this regard, it is noted that the only cylinders 42 are capable of setting in motion all of the parts of the module, so that no additional actuator is provided in the casing 28. The latter can thus have a reduced dimensioning , positively impacting the design of the rest of the nacelle.
    The inversion grid 46 may be of conventional planar shape, or else slightly rounded in the circumferential direction. It conventionally comprises orifices through which the air of the secondary channel 24 is intended to circulate, when the reverser system 40 is in the active configuration. It is capable of redirecting a stream of air passing through it forward, by means of fins or similar elements defined between the orifices.
    Under the grid 46, the reverser system 40 comprises the reverser door 50, preferably substantially planar and produced in one piece. In the inactive configuration, the door 50 is substantially parallel to the grid 46, and this door is also located at least in part radially opposite the fan casing 8.
    The door 50 has a conventional design, capable in active configuration of closing at least partially the secondary channel 24, as will be described later.
    In addition to the grid 46 and the door 50, the reverser system 40 comprises two connecting parts making it possible to obtain the kinematics and the synchronization desired for the door and the grid.
    It is first of all a first connecting part 52a, in the overall shape of an L, a first end of which is connected to the inside of the cowling 28 by a first articulated connection L1. In fact, the cowling 28 has a hollow body opening towards the front, which is partly defined by the inner wall 26 of the secondary channel 24. It is on this wall 26, inside the hollow that it defines that the first end of the first connecting part 52a is hinged. Its second end, opposite the first, is connected to a central portion of the inverter door 50 by a second articulated link L2. These two links L1 and L2, like all the other links which will be described below, define pivot axes which are all substantially parallel to each other within the same reverser module. These pivot axes are preferably orthogonal to the longitudinal axis 6, and oriented tangentially.
    It is then a second connecting piece 52b, a first end of which is connected to a rear end of the inverter door 50, using a third articulated link L3. Its second end, opposite the first, is connected to the inner wall 22 of the secondary channel 24 by a fourth articulated link L4, close to the outer shell 14 of the intermediate casing. The second connecting piece 52b has a generally straight shape, like a connecting rod, the first end of which may possibly be slightly inclined relative to the rest of the connecting rod. In the inactive configuration, this brings it closer to the rear end of the door 50 on which it is hinged.
    In the inactive configuration of the inverter system 40, the first connecting part 52a, the grid 46 and the door 50 are thus entirely arranged in a housing space 60, defined by the nacelle outside the secondary channel 24, in the thickness of the nacelle. The secondary channel 24 is therefore not disturbed by the presence of these elements, and the outer wall 26 delimiting the secondary channel 24 can therefore be continuous, for example by being made in one piece. This significantly improves the overall aerodynamic performance of the turbomachine.
    The housing space 60 is partly defined by the hollow of the fan cowls 32, as well as by the hollow of the external movable cowling 28 located in the rear axial continuity of the hollow of the fan cowls 32. In the inactive configuration, this space 60 also houses the jack 42, as well as the first end of the second connecting part 52b. The other part of the second connecting piece 52b is located substantially radially in the secondary channel 24, and substantially close to a rear plane of the intermediate casing 10. Each connecting piece 52b is masked from the air flow secondary crossing the channel 24, by an aerodynamic structural arm 16 of this casing 10 which is radially contained in the same plane, as shown in FIG. 4. Consequently, due to its particular position in the continuity of one of these arms 16, the second connecting part 52b generates only very little disturbance of the secondary air flow.
    In addition, the inverter door 50 is mounted at its front end on the grid 46 by a fifth link L5, the second link L2 thus being arranged between the third link L3 and this fifth link L5. The latter comprises one or more guide rails 62 integral with the grid, preferably taking the form of oblong grooves made directly in this same grid, along, in the thickness and on each side thereof. Each rail 62 extends axially parallel to the grid 46, and cooperates with a roller 64 mounted on the front end of the reverser door 50.
    Thanks to this fifth link L5, the front end of the door 50 is capable, simultaneously, of sliding along the grid 46 and of pivoting with respect thereto.
    In this regard, it is specified that the modules of the reverser system can be connected to each other at the level of the grids, by the rollers 64. Each of these rollers can in fact be part of mechanical connection means provided between the grids 46 directly consecutive in the tangential direction. These grids are moreover provided in a sufficient number so that they form an assembly extending over an angular sector of 300 to 360 ° around the longitudinal axis 6 of the turbomachine. As an indicative example, it may for example be a number of grids between 4 and 12. The same is true for the inverter doors, which are intended to obstruct the same angular sector of the secondary channel. 24, in active configuration of the reversing system.
    In this case, since the grids 46 are fixed to each other, it is not necessary to provide a jack 42 for each module, so that the number of these jacks 42 may be less than the number of gates. By way of example, there is provided a jack 42 every two grids 46 along the tangential direction. In the mode shown in FIG. 4, there are provided nine grids 46 and only three cylinders 42.
    One of the particularities of the invention resides in the fact that the actuation of the jacks 42 causes all of the parts of the thrust reverser system to move, without it being necessary to provide means additional actuation. This particular so-called “in-line” arrangement makes it possible to benefit from a simplicity of design, which moreover limits the overall mass of the thrust reverser system and therefore increases the overall performance of the turbomachine.
    In operation, when each actuator 42 is actuated so as to pass from the inactive configuration to the active configuration, the actuator rod 43 is pulled back as shown in FIG. 5 showing an intermediate configuration between the inactive configuration , and the active configuration.
    The output of the actuator rod 43, combined with the tilting and driving actions caused by the connecting pieces 52a, 52b, produce different movements which will now be described with reference to FIG. 5 showing an intermediate configuration, and to the Figures 6 to 8 showing the active configuration.
    It is in fact observed a rearward displacement of the grid 46, directly due to the action of the jack rod 43. This displacement is a translation in the direction X, which causes the grid 46 to enter an opening nacelle 70 which is gradually released by the external movable cowling 28. The latter undergoes the same movement as the grid 46.
    Simultaneously, the inverter door 50 undergoes a combined movement relative to the grid 46, always in movement. This combined movement, dictated in particular by the connecting pieces 52a, 52b, leads to the displacement of the front end of the door 50 backwards along the grid 46. It also leads to the pivoting of this door 50 according to the fifth link L5, around the axis of the rollers 64. This pivoting causes the rear end of the door 50 to sink into the secondary channel 24.
    The judiciously positioned elements of the system 40 thus allow perfect synchronization of movements so that the door 50 can exit from the space 60 in which it is arranged axially, while gradually plunging towards the interior of the secondary channel 24, until lead to a substantially radial position as visible in Figures 6 to 8. In the active configuration shown in these figures, the grid 46 and the door 50 are arranged substantially orthogonally to each other. In addition, the front end of the door 50 (corresponding to its radially external end in the active configuration), is always connected to the grid 46 by the fifth link L5, at a rear end of this grid up to which this L5 link has moved. The door 50 thus remains entirely under the grid 46, the latter filling the opening 70 without plunging into the channel 24. This advantageously implies a blockage of the air flow in the channel 24 and forces its passage through the grid 46.
    During these movements, the two connecting pieces 52a, 52b fulfill their function of rocking and driving the door 50. The second connecting piece 52b thus pivots according to the fourth articulated link L4, until reaching a position where it is locally substantially parallel and pressed against the inner wall 22 of the secondary channel. The disturbances in the secondary flow caused by these connecting pieces 52b are minor. Also, the base of the L of the first connecting part 52a is pressed against the movable outer wall 26, inside the cover 28, while the branch of the L is extracted from the space 60 and protrudes slightly in the channel. secondary 24 and behind the door 50 which closes, at least partially, the aerodynamic vein 24.
    Of course, various modifications can be made by those skilled in the art to the invention which has just been described, only by way of nonlimiting examples.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. thrust reverser system (40) for a turbomachine (1) of an aircraft with double flow, the reverser system comprising at least one thrust reversing grid (46) through which is intended to circulate the air from a secondary channel (24) of the turbomachine in the active configuration of the inverter system, this also comprising at least one inverter door (50) configured to at least partially close said secondary channel (24) when the system is in active configuration, the system also comprising at least one actuating cylinder (42), characterized in that in an inactive configuration of the reversing system, the door (50) is housed in a housing space (60) located outside said secondary channel (24) and in which there is also said grid (46) driven by said jack (42) and one rear end of which is secured to an external mobile nacelle cowling (28), the system also comprising:
    - A first connecting part (52a), a first end of which is connected to the interior of said external movable nacelle cowling (28) by a first articulated connection (Ll), and a second end of which is connected to the reverser door (50) by a second articulated link (L2);
    - a second connecting part (52b), a first end of which is connected to a rear end of the inverter door (50) by a third articulated connection (L3), and a second end of which is connected to an interior wall (22 ) of the secondary channel (24) by a fourth articulated link (L4);
    and in that the reverser door (50) is mounted at its front end on the grid by a fifth link (L5) allowing this front end to slide along the grid (46) and pivot relative to that -this, the second articulated link (L2) being arranged between the third articulated link (L3) and the fifth link (L5) so that during a transition from the inactive configuration to the active configuration, the presence of the first and second connecting parts (52a, 52b) combined with the action of said jack (42) simultaneously produce:
    - A rearward movement of the grid (46) in the direction of a nacelle opening (70), released by the external mobile nacelle cowling (28) driven rearward with the grid (46); and
    - A combined movement of the inverter door (50) relative to the grid (46) leading on the one hand to the displacement of the front end of the door (50) backwards along the grid (46) , and secondly to the pivoting of this door according to the fifth link (L5) so as to cause the plunging of its rear end into the secondary channel (24).
    [2" id="c-fr-0002]
    2. Inverter system according to claim 1, characterized in that in the inactive configuration, the first connecting part is housed in the housing space (60), and in that the second connecting part is housed in part in this accommodation space (60).
    [3" id="c-fr-0003]
    3. Inverter system according to any one of the preceding claims, characterized in that in the inactive configuration, part of the second connecting part (52b) is arranged substantially radially in the secondary channel (24), and preferably intended to be masked from a secondary air flow by an arm (16) of an intermediate casing of the turbomachine, and in that in the active configuration, said second connecting piece (52b) is arranged locally substantially parallel to the inner wall (22) of the secondary channel.
    [4" id="c-fr-0004]
    4. Inverter system according to any one of the preceding claims, characterized in that the first connecting part (52a) adopts an overall shape of an L.
    [5" id="c-fr-0005]
    5. Inverter system according to any one of the preceding claims, characterized in that the jack comprises a jack rod (43) articulated on a front end of the grid (46).
    [6" id="c-fr-0006]
    6. Inverter system according to any one of the preceding claims, characterized in that the fifth link (L5) comprises at least one guide rail (62) of door integral with the grid and extending along it- ci, as well as a roller cooperating with this rail and mounted on the front end of the inverter door (50).
    [7" id="c-fr-0007]
    7. Inverter system according to any one of the preceding claims, characterized in that said housing space (60) is an interior space of the nacelle (30).
    [8" id="c-fr-0008]
    8. Inverter system according to any one of the preceding claims, characterized in that in its inactive configuration, the grid (46) and the inverter door (50) are substantially parallel and are each located at least partly in radially looking from a fan casing (8) of the turbomachine.
    [9" id="c-fr-0009]
    9. Inverter system according to any one of the preceding claims, characterized in that it comprises several grids (46) adjacent in the tangential direction of the turbomachine, preferably so as to form a set of grids extending over an angular sector of 300 to 360 ° around a longitudinal axis (6) of the turbomachine, and in that each grid (46) is associated with an inverter door (50).
    [10" id="c-fr-0010]
    10. Inverter system according to the preceding claim, characterized in that the grids (46) are mechanically connected to each other so that the number of cylinders (42) is preferably less than the number of grids.
    [11" id="c-fr-0011]
    11. aircraft turbomachine (1) with double flow comprising a thrust reverser system (40) according to any one of the preceding claims.
    [12" id="c-fr-0012]
    12. Aircraft (100) comprising at least one turbomachine (1) according to the preceding claim.
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    US10533519B2|2016-01-13|2020-01-14|Rohr, Inc.|Translating cascade hidden blocker door thrust reverser|
    US10428764B2|2016-02-10|2019-10-01|Rohr, Inc.|Deflection limiter for a cascade assembly of a thrust reverser|
    FR3055669B1|2016-09-05|2018-09-28|Airbus Operations|THRUST INVERTER SYSTEM LIMITING AERODYNAMIC DISTURBANCES IN CONFIGURATION INACTIVE|
    US10724475B2|2016-09-27|2020-07-28|The Boeing Company|Dual turn thrust reverser cascade systems and methods|
    FR3057618A1|2016-10-17|2018-04-20|Airbus|NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER|FR3068081B1|2017-06-21|2020-10-16|Airbus Operations Sas|PUSH-INVERTER SYSTEM WITH LIMITED AERODYNAMIC INTERRUPTION|
    FR3068394B1|2017-06-29|2019-07-19|Airbus Operations|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH INVERTER SHUTTERS|
    FR3090579A1|2018-12-20|2020-06-26|Airbus Operations|NACELLE OF A TURBOREACTOR COMPRISING A REVERSING SHUTTER AND A DELAYED DEPLOYMENT SYSTEM|
    法律状态:
    2018-12-14| PLSC| Publication of the preliminary search report|Effective date: 20181214 |
    2020-06-19| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1755315|2017-06-13|
    FR1755315A|FR3067406B1|2017-06-13|2017-06-13|THRUST INVERTER SYSTEM HAVING LIMITED AERODYNAMIC DISTURBANCES|FR1755315A| FR3067406B1|2017-06-13|2017-06-13|THRUST INVERTER SYSTEM HAVING LIMITED AERODYNAMIC DISTURBANCES|
    EP18174500.1A| EP3415749B1|2017-06-13|2018-05-28|Nacelle with thrust reverser system creating limited aerodynamic disturbances|
    US16/001,331| US10731602B2|2017-06-13|2018-06-06|Thrust reverser system exhibiting limited aerodynamic perturbation|
    CN201810580361.6A| CN109080836A|2017-06-13|2018-06-07|Thrust reverser system and turbogenerator and aircraft|
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