• 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:
    In order to reduce aerodynamic disturbances in a secondary channel of a dual-flow aircraft turbomachine, the invention provides a thrust reverser system (40) comprising a thrust reversal gate (46) and a thrust reverser gate (46). inverter made using door sections (50a, 50b) arranged in a folded state relative to each other in an inactive configuration of the inverter system, and housed in a housing space (60) located outside the secondary canal (24). Also, the system is configured so that it occurs simultaneously, during a transition from the inactive configuration to the active configuration: a rearwards movement of the grid towards a nacelle opening (70) , released by an outer movable cowl of platform (28) driven rearwardly by the grid; - Deployment of the sections (50a, 50b) until they reach an extended position of closure within the secondary channel.
    公开号:FR3055669A1
    申请号:FR1658213
    申请日:2016-09-05
    公开日:2018-03-09
    发明作者:Olivier Pautis；Jerome Colmagro
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    DESCRIPTION
    TECHNICAL AREA
    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 turbofan turbines.
    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 outer wall of the secondary channel, also known as 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 movable 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 the active configuration of the inverter system, the latter also comprising at least one inverter door configured to at least partially close said secondary channel downstream of the grid reverse thrust, when the system is in active configuration.
    According to the invention, the inverter door is produced using at least two door sections arranged in a folded state relative to each other in an inactive configuration of the inverter system, and housed in a housing space located outside said secondary channel and in which there is also said grid to which is connected at least one of said two door sections.
    In addition, the inverter system is configured so that it occurs simultaneously, when switching from the inactive configuration to the active configuration:
    - a rearward movement of the grid in the direction of a nacelle opening, released by an external mobile nacelle cowling driven rearward by the grid, via at least one of the two door sections; and
    - Deployment of said two door sections relative to each other, until they reach a deployed position of closure within the secondary channel.
    The invention thus contrasts with the conventional embodiments of grid inverter systems, by providing an inverter door in several sections arranged outside the secondary channel in the inactive configuration of the system, and which deploy in the annular channel during passage to the active configuration. Thanks to this design specific to the present invention, when the system is in the inactive configuration, the inverter doors no longer disturb the air flow passing through the secondary channel of the turbomachine. Advantageously, this improves the overall performance of the turbomachine.
    The invention provides at least one of the following optional characteristics, taken individually or in combination.
    In its active configuration, the grid is inclined relative to a longitudinal axis of the turbomachine so that its rear end is housed inside the secondary channel, and the two door sections project from this rear end respectively radially inward and outward, in the secondary canal.
    In the active configuration of the system, one of the two door sections forces the air from the secondary channel to escape through the grid, and the other of the two door sections prevents the air exited by the grid from recirculating in said grid. secondary channel, the two door sections preferably being substantially aligned in the active configuration of the system.
    The reverser system preferably includes:
    - A first door section, one end of which is hinged to the rear end of the grid, and one opposite end of which is secured to a first end of a first connecting piece, the second opposite end of which is hinged to the inside said external mobile nacelle cowling, the first door section and the first connecting part being preferably made in one piece;
    - a second door section, one end of which is hinged to the rear end of the grid, and one opposite end of which is secured to a first end of a second connecting piece, the second opposite end of which is intended to be hinged on an inner wall of the secondary channel, also called IFS (from the English “Inner Fixed Structure”), the second door section and the second connecting part being preferably made in one piece.
    By way of example, the first connecting part has a general shape of U or yoke, and the second connecting part is a connecting rod. Other forms are nevertheless possible, without departing from the scope of the invention.
    In the inactive configuration of the system, 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, preferably a output director vane and even more preferably such a vane with an additional structural function. In addition, in the active configuration, said second connecting piece is arranged locally substantially parallel to the inner wall of the secondary turbomachine channel.
    In longitudinal section, the assembly formed by the first door section and the first connecting piece takes the overall shape of an L, and the assembly formed by the second door section and the second connecting piece also takes the form overall of an L.
    In longitudinal section, the assembly formed by the grid and the first and second sections takes the overall form of a Y in the inactive configuration, and a T in the active configuration.
    The reversing system comprises at least one actuator for setting the grid in motion, towards the front and towards the rear, the actuator comprising a cylinder rod preferably articulated on a front end of the grille, and it also comprises at least one grid guide rail intended to be integral with a casing of the turbomachine, and preferably several rails cooperating with a front end of the grid.
    Said accommodation space is an interior space of the nacelle.
    In its inactive configuration, the grid is located at least partially radially opposite a fan casing of the turbomachine.
    The reverser system comprises several adjacent grids in the tangential direction of the turbomachine, preferably so as to form a set of grids extending over substantially 360 ° around a longitudinal axis of the turbomachine, and each grid is associated with an inverter door.
    Finally, 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 a double-flow aircraft 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;
    - 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 ferrule 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 known as the core casing, referenced 18 in FIG. 4 and containing the core of the turbomachine. Around the central casing, there is an inter-vein compartment 20 delimited by a fixed internal cover.
    22, also known as 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 extending towards the rear, therefore being delimited internally by the wall 22, and externally by an external wall of the secondary channel 26. This is integrated into an external mobile nacelle cowling 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 forward and backwards 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 the arrow 34.
    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 to each other in the tangential direction of the turbomachine, all around the axis 6. At least some of these modules each comprise, in the front part, a jack 42, one front end of which is mounted for example articulated on the front end of the fan casing 8. The jack 42 comprises a jack rod 42 which is mounted so articulated at its front end to a thrust reversing grid 46. In the inactive configuration, the grid 46 is located radially outwards, facing the fan casing 8 and the outer shroud 14 of the intermediate casing. Therefore, in this configuration, the grid is located in front of the external movable cowling
    28, and therefore does not enter the latter. The grid 46 and the jack 42 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 makes it possible to benefit from more room for their integration. This advantageously results in a nacelle 30 of reduced outside diameter.
    The inversion grid 46 can be of conventional flat shape, or alternatively have two sections which are substantially inclined relative to one another, as shown in the section in FIG. 2. It conventionally comprises orifices at through which the air of the secondary channel 24 is intended to circulate, when the inverter system 40 is in the active configuration.
    At the rear of the grid, the reverser system 40 comprises two sections of reverser door, intended to reconstitute and thus together form the reverser door, when the system adopts its active configuration as will be described below.
    It is a first door section 50a, one front end of which is articulated on the rear end of the grid 46. This first door section 50a is substantially planar, and substantially parallel to the longitudinal axis 6 in s 'extending to a rear end secured to a first connecting part 52a. More specifically, the rear end of the first door section 50a is integral with an upper end 54a of the first connecting part 52a, the latter having a second opposite end 56a, called the internal end, articulated on the external movable cowling 28 .
    Indeed, the cowling 28 has a hollow body opening towards the front, which is partly defined by the internal wall 26 of the secondary channel 24. It is on this wall 26, inside the hollow that it defines that the end 56a of the first connecting piece 52a is hinged. This first connecting part 52a is produced in one piece with the first door section 50a, for which it fulfills a rocker function, as will be described below. In longitudinal section as shown in FIG. 2, the assembly formed by these two elements 50a, 52a takes the general form of a lying L, with the base of the L oriented radially inwards. As is best visible in Figure 3, the connecting piece 52a has a general shape of U or yoke, of width less than that of the door section 50a.
    Thus, in the inactive configuration of the reverser system, the first door section 50a as well as the first connecting piece 52a are both arranged in a housing space 60, defined by the nacelle outside the secondary channel 24, in the 'own thickness of the nacelle. The secondary channel 24 is therefore not disturbed by the presence of these elements 50a, 52a, and the outer wall 26 delimiting the secondary channel 24 can therefore be continuous, for example by being made in one piece.
    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 axial continuity of the hollow of the fan cowls 32. In the inactive configuration, the grid 46 is is also found in this housing space 60, just like the jack 42.
    Furthermore, the second door section 50b, one front end of which is also articulated on the rear end of the grid 46, is substantially planar and slightly inclined relative to the longitudinal axis 6. It extends to a rear end secured to a second connecting piece 52b. More specifically, the rear end of the second door section 50b is integral with an upper end 54b of the second connecting part 52b, the latter having an opposite second end 56b, called the inner end, articulated on the fixed inner wall 22 .
    The second connecting part 52b is made in one piece with the second door section 50b, for which it fulfills a rocker function, as will also be described below. In longitudinal section as shown in FIG. 2, the assembly formed by these two elements 50b, 52b takes the general form of an inverted L, with the base of the L facing forward. As is best visible in FIG. 3, the second connecting part 52b has a general form of connecting rod, connected in a centered manner on the second door section 50b.
    Thus, in the inactive configuration of the reverser system, the second door section 50b is arranged in the housing space 60 defined by the nacelle, outside the secondary channel 24. The second connecting part 52b is located as for it is arranged substantially radially in the secondary channel 24, in close proximity to the intermediate casing 10. It is in fact masked from the secondary air flow passing through the channel 24, by one of the structural aerodynamic arms 16 of this casing 10, like this is shown in Figure 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, it is noted that all of the articulated elements of the kinematic chain described above have articulation axes oriented substantially in the tangential direction of the turbomachine.
    In the inactive configuration of the inverter system, the two door sections 50a, 50b are therefore arranged outside the secondary channel 24, in a folded state relative to each other. This state corresponds to a fold-back position in the portfolio, in which they are inclined at a small angle to each other. They are arranged in the rear continuity of the grid 46, also located in the housing space 60 of the nacelle, so that in the inactive configuration, these three elements 46, 50a, 50b take the general shape of a lying Y .
    As is best visible in FIG. 3, the fan casing 8 is equipped with longitudinal rails 62 serving to guide the front end of the grate 46. To do this, this front grate end can be equipped with rollers capable to slide in a groove 64 of each rail 62. In this regard, it is specified that the modules of the reverser system can be connected to each other at the level of these rollers (not shown), each of which can indeed 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 substantially 360 ° all around the longitudinal axis 6 of the turbomachine. As an indicative example, it may for example be a number of grids between 6 and 12. The same is true for the inverter doors, which are intended to substantially obstruct 360 ° of the secondary channel in active configuration of the inverter 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.
    The rails 62 are in turn arranged between the modules, which therefore each comprise a grid 46 as well as a single inverter door formed by the two sections 50a, 50b, the angular extent of which is substantially identical to that of the grid. .
    One of the features 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 arrangement known as "in line" allows to benefit from a simplicity of design, which moreover limits the overall mass of the turbomachine.
    In operation, when each jack 42 is actuated so as to pass from the inactive configuration to the active configuration, the jack rod 44 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 44 firstly causes the rearward movement of the grid 46 guided by the rails (not shown in FIG. 5). This rearward movement is transmitted to the external movable cowling 28 via the first door section 50a, and by the first connecting piece 52a. During these rearward displacements, the two connecting pieces 52a, 52b fulfill their rocking function and drive by pivoting the rear end of the grid 46 radially inwards, in the secondary annular channel 24. This grid 46 therefore undergoes a longitudinal displacement towards the rear under the effect of the action of the jack 42, but also plunges radially inwards towards the internal wall 22 of the secondary channel 24. By moving towards the rear, the grid 46 progressively enters a nacelle opening 70 which is gradually released by the external movable cowling 28, also moving backwards. More precisely, this opening 70 is defined between the front end of this cowling 28, and the rear end of the fan cowls 32.
    In addition, the connecting pieces 52a, 52b also have the consequence, because of their tilting function, of deploying the two door sections 50a, 50b so that the angle 51 which they form increases, like this. is shown in Figure 5.
    When the actuator rod 44 is fully deployed, the active configuration of the reversing system 40 is reached, and the two door sections 50a, 50b then adopt a deployed position in which the reverser door 50 is reconstituted so as to close off the secondary channel 24, as shown in FIGS. 6 to 8.
    In this configuration, the grid 46 and the two door sections 50a, 50b adopt a general shape of a coated T, since the two door sections 50a, 50b are preferably substantially aligned with respect to each other. However, as shown in FIG. 6, a small angle may remain between the two door sections 50a, 50b, for example an angle less than 15 °. It is noted that other relative provisions could be adopted in the active configuration of the reverser system, for example by providing that the two door sections 50a, 50b form a V open towards the front.
    The second section 50b here fulfills a barrier function aimed at forcing the air leaving the secondary channel 24 through the intermediate casing, to necessarily escape through the grid 46, without being able to flow further downstream in this secondary channel 24. The second section 50b projects radially inwards from the rear end of the grid 46, inclined relative to the longitudinal axis 6, for example by an angle between 30 and 60 °.
    In this configuration, the second connecting element 52b is substantially parallel and pressed against the inner wall 22 of the secondary channel, so that the disturbances in the secondary flow caused by these connecting parts 52b are minor. Also, the first connecting piece 52a is pressed against the movable outer wall 26, inside the cowling 28. The two connecting pieces 52a, 52b are thus substantially parallel to the axis 6, while the two sections 50a, 50b are substantially aligned and orthogonal to this same axis 6.
    The first door section 50a fulfills not only a function of guiding the air after its exit through the grid 46, but also a function aimed at preventing the air exited by this grid from recirculating in the secondary channel 24. It in fact forms a barrier connecting the rear end of the grid 46 to the cowling 28 in the withdrawn position. Thus, as shown diagrammatically in FIG. 6, the air from the secondary flow leaving the intermediate casing 10 is forced by the second door sections 50b to pass through the orifices of the grid 46, so that the air flow secondary is reversed. The flow leaving the grid is prevented from reintegrating the secondary channel 24, due to the presence of the first door section 50a which extends in turn radially outward from the rear end of the grid 46.
    Preferably, the rear end of the grid 46 is situated substantially centered in the secondary annular channel 24, in the radial direction. However, depending on the needs encountered, this rear end could be brought closer to the outer wall 26 or alternatively brought closer to the inner wall 22 of the secondary channel 24, without departing from the scope of the invention.
    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. As an indicative example, the particular kinematics described below could be modified by providing that only the first door section 50a is articulated on the rear end of the grid, and with the second door section 50b articulated on this same first section 50a.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    1. thrust reverser system (40) for a turbomachine (1) of a double-flow aircraft, 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) downstream of the thrust reversing grid (46), when the system is in the active configuration, characterized in that the reverser door (50) is produced using at least two door sections (50a, 50b) arranged in a collapsed state relative to each other in an inactive configuration of the inverter system, and housed in a housing space (60) located outside said secondary channel (24) and in which is also located said grid (46) to which at least one of said two sections is connected door (50a, 50b), and in that the reverser system is configured so that it occurs simultaneously, when switching from the inactive configuration to the active configuration:
    - a rearward movement of the grid (46) in the direction of a nacelle opening (70), released by an external mobile nacelle cowling (28) driven rearward by the grid (46), via at minus one of the two door sections (50a, 50b); and
    - Deployment of said two door sections (50a, 50b) relative to each other, until they reach a deployed position of closure within the secondary channel (24).
    [2" id="c-fr-0002]
    2. Inverter system according to claim 1, characterized in that in its active configuration, the grid (46) is inclined relative to a longitudinal axis (6) of the turbomachine so that its rear end is housed at inside the secondary channel (24), and the two door sections (24a, 24b) project from this rear end respectively radially inward and outward, into the secondary channel (24).
    [3" id="c-fr-0003]
    3. Inverter system according to claim 2, characterized in that in the active configuration of the system, one of the two door sections (50b) forces the air from the secondary channel (24) to escape through the grid. (46), and the other of the two door sections (50a) prevents the air exited by the grid (46) from recirculating in said secondary channel (24), the two door sections preferably being substantially aligned in the configuration active system.
    [4" id="c-fr-0004]
    4. Inverter system according to any one of the preceding claims, characterized in that it comprises:
    - A first door section (50a), one end of which is hinged to the rear end of the grid (46), and one opposite end of which is secured to a first end (54a) of a first connecting piece (52a ), the second opposite end (56a) of which is articulated inside said external movable nacelle cowling (28), the first door section (50a) and the first connecting part (52a) being preferably made in one holding;
    - A second door section (50b), one end of which is articulated on the rear end of the grid (46), and one opposite end of which is integral with a first end (54b) of a second connecting piece (52b ), the second opposite end (56b) of which is intended to be articulated on an inner wall (22) of the secondary channel (24), the second door section (50b) and the second connecting part (52b) being preferably made of '' in one piece.
    [5" id="c-fr-0005]
    5. Inverter system according to claim 4, characterized in that the first connecting piece (52a) has a general shape of U or yoke, and the second connecting piece (52b) is a connecting rod.
    [6" id="c-fr-0006]
    6. Inverter system according to claim 4 or claim 5, characterized in that in the inactive configuration of the system, 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 part (52b) is arranged locally substantially parallel to the inner wall (22) of the secondary channel.
    [7" id="c-fr-0007]
    7. Inverter system according to any one of claims 4 to 6, characterized in that in longitudinal section, the assembly formed by the first door section (50a) and the first connecting piece (52a) takes the overall shape of an L, and in that the assembly formed by the second door section (50b) and the second connecting piece (52b) also takes the overall shape of an L.
    [8" id="c-fr-0008]
    8. Inverter system according to any one of claims 4 to 7, characterized in that in longitudinal section, the assembly formed by the grid (46) and the first and second door sections (50a, 50b) takes the global form of a Y in an inactive configuration, and a T in an active configuration.
    [9" id="c-fr-0009]
    9. Inverter system according to any one of the preceding claims, characterized in that it comprises at least one jack (42) for setting the grid in motion (46), towards the front and towards the rear, the jack comprising a jack rod (44) preferably articulated on a front end of the grid (46), and in that it also comprises at least one guide rail (62) of the grid intended to be integral with a casing (8) of the turbomachine, and preferably several rails (62) cooperating with a front end of the grid (46).
    [10" id="c-fr-0010]
    10. Inverter system according to any one of the preceding claims, characterized in that said housing space (60) is an interior space of the nacelle.
    [11" id="c-fr-0011]
    11. Inverter system according to any one of the preceding claims, characterized in that in its inactive configuration, the grid (46) is located at least partially facing radially from a fan casing (8) of the turbomachine .
    5
    [12" id="c-fr-0012]
    12. 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 substantially 360 ° around a longitudinal axis (6) of the turbomachine, and in that each grid (46) is associated with an inverter door (50).
    [13" id="c-fr-0013]
    13. Inverter system according to the preceding claim combined with claim 9, 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.
    [14" id="c-fr-0014]
    14. Aircraft turbomachine (1) with double flow comprising a thrust reverser system (40) according to any one of the preceding claims.
    [15" id="c-fr-0015]
    15. Aircraft (100) comprising at least one turbomachine (1) according to the preceding claim.
    .61100
    1/4
    100
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    EP3548380A1|2019-10-09|Jet engine nacelle , propulsion assembly and aircraft comprising such a nacelle
    WO2009112749A2|2009-09-17|Thrust reverser for bypass turbojet engine nacelle
    FR2997925A1|2014-05-16|GUIDE ASSEMBLY FOR A MOBILE NACELLAL UNIT FOR A TURBOJET ENGINE
    EP2841340B1|2016-04-13|Turbofan engine nacelle with downstream section
    WO2021234279A1|2021-11-25|Nacelle for a propulsion assembly with a very high bypass ratio, comprising a removable and structural front internal structure
    同族专利:
    公开号 | 公开日
    GB2555924A|2018-05-16|
    CN107795406B|2021-12-31|
    GB201714142D0|2017-10-18|
    CN107795406A|2018-03-13|
    US10519899B2|2019-12-31|
    FR3055669B1|2018-09-28|
    US20180066606A1|2018-03-08|
    GB2555924B|2021-02-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3981451A|1975-11-17|1976-09-21|Rohr Industries, Inc.|Fan cascade thrust reverser|
    US20090321561A1|2008-06-26|2009-12-31|Airbus France|Nacelle for aircraft comprising means of reversing thrust and aircraft comprising at least one such nacelle|
    DE102013206595A1|2013-04-12|2014-10-16|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Jet engine|
    EP2921685A2|2014-03-21|2015-09-23|Rohr, Inc.|Thrust reverser for a turbofan engine|
    US5706649A|1995-04-03|1998-01-13|Boeing North American, Inc.|Multi axis thrust vectoring for turbo fan engines|
    FR2914700B1|2007-04-04|2009-05-22|Aircelle Sa|THRUST INVERTER FOR REACTION ENGINE|
    FR2935444B1|2008-09-02|2010-09-10|Airbus France|THRUST INVERTER AND NACELLE FOR AN AIRCRAFT PROVIDED WITH AT LEAST ONE SUCH INVERTER|
    FR2935354B1|2008-09-02|2011-04-01|Airbus France|NACELLE FOR DOUBLE FLOW MOTOR|
    US9016040B2|2012-11-30|2015-04-28|General Electric Company|Thrust reverser system with translating-rotating cascade and method of operation|
    US20160076484A1|2013-06-07|2016-03-17|Aircelle|Turbojet engine nacelle thrust reverser comprising cascades secured to the mobile cowls|
    GB201314527D0|2013-08-14|2013-09-25|Rolls Royce Deutschland|Thrust reverser unit|
    US10309343B2|2014-11-06|2019-06-04|Rohr, Inc.|Split sleeve hidden door thrust reverser|
    US10041443B2|2015-06-09|2018-08-07|The Boeing Company|Thrust reverser apparatus and method|
    FR3040076B1|2015-08-13|2017-08-11|Airbus Operations Sas|AIRCRAFT ENGINE ASSEMBLY COMPRISING A PRIMARY STRUCTURE OF A COUPLING MAT EQUIPPED WITH A BOX EXTENSION COMPRISING TWO PARTS IN GLOBAL ARCEAU SHAPE|
    US10378479B2|2015-10-19|2019-08-13|General Electric Company|Variable effective area fan nozzle|
    FR3047973B1|2016-02-23|2018-03-09|Airbus Operations|AIRCRAFT ENGINE ASSEMBLY, COMPRISING A MOTOR ATTACHING DEVICE EQUIPPED WITH STRUCTURAL MOBILE HOOKS CONNECTED TO THE CENTRAL CABIN|FR3067406B1|2017-06-13|2019-07-12|Airbus Operations|THRUST INVERTER SYSTEM HAVING LIMITED AERODYNAMIC DISTURBANCES|
    FR3068081B1|2017-06-21|2020-10-16|Airbus Operations Sas|PUSH-INVERTER SYSTEM WITH LIMITED AERODYNAMIC INTERRUPTION|
    FR3082889A1|2018-06-26|2019-12-27|Airbus Operations|TURBOREACTOR COMPRISING A NACELLE EQUIPPED WITH REVERSING SHUTTERS PROVIDED WITH MEANS FOR GENERATING VORTS|
    法律状态:
    2017-09-28| PLFP| Fee payment|Year of fee payment: 2 |
    2018-03-09| PLSC| Publication of the preliminary search report|Effective date: 20180309 |
    2018-09-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-09-26| PLFP| Fee payment|Year of fee payment: 4 |
    2020-09-14| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1658213A|FR3055669B1|2016-09-05|2016-09-05|THRUST INVERTER SYSTEM LIMITING AERODYNAMIC DISTURBANCES IN CONFIGURATION INACTIVE|
    FR1658213|2016-09-05|FR1658213A| FR3055669B1|2016-09-05|2016-09-05|THRUST INVERTER SYSTEM LIMITING AERODYNAMIC DISTURBANCES IN CONFIGURATION INACTIVE|
    US15/693,735| US10519899B2|2016-09-05|2017-09-01|Thrust reverser system limiting aerodynamic perturbation in an inactive configuration|
    GB1714142.5A| GB2555924B|2016-09-05|2017-09-04|Thurst Reverser System Limiting Aerodynamic Perturbations In An Inactive Configuration|
    CN201710790898.0A| CN107795406B|2016-09-05|2017-09-05|Thrust reverser system limiting aerodynamic disturbances in a deactivated configuration|
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