• 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 aid its deployment, the invention proposes a deployable gate (32) with fins (44) for an aircraft engine turbomachine thrust reversal system (6), the gate being capable of adopting a rest position. and an active position deployed in which the fins (44) are further spaced axially from each other than in the rest position. The grid comprises, at least between two fins (44), elastic return means (56) forcing said two fins (44) to deviate axially from one another.
    公开号:FR3027065A1
    申请号:FR1459801
    申请日:2014-10-13
    公开日:2016-04-15
    发明作者:Jeremy Edmond Fert
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to the field of aircraft engine turbomachine thrust reversal systems, and more particularly to the field of finned grids equipping the aircraft turboshaft thrust reverser systems. such systems.
    [0002] The invention applies to any type of aircraft turbomachine, preferably to turbojet engines. STATE OF THE PRIOR ART From the prior art, it is known to use finned grids to form thrust reversal systems. In these systems, the fins take the form of deflectors for redirecting forward part of the air flow from the secondary vein of the turbojet engine. The reversal of the direction of this airflow contributes to the braking of the aircraft during landing. Deployable grids are particularly known from FR 2 947 869. With this type of design, in the rest position of the grid, the fins are stacked and occupy a small space. The length of the inverter is thus reduced, which results in a gain in terms of mass and aerodynamic performance. The document FR 2,588,312 also proposes an inverter gate that can be deployed. One of the peculiarities lies in the ability to move, downstream, the movable nacelle cover element, after the gate has reached its deployed active position. Thanks to this movement, the grid can be entirely discovered during the phases of thrust reversal. However, in this thrust reversal system, the deployment of the fins is performed under the unique effect of the aerodynamic force 3027065 2 applying on these fins. Therefore, this technical solution is likely to suffer from a problem of reliability, since there is a risk that the air from the secondary vein fails to generate such a deployment of the grid. To mitigate this risk, it is possible to adapt the shape of the fins, and / or to arrange them in a particular way in order to favor the deployment of the grid, under the effect of the aerodynamic force applied by the secondary air. However, these adjustments may adversely affect thrust reversal performance. DISCLOSURE OF THE INVENTION The object of the invention is therefore to remedy at least partially the disadvantages relating to the embodiments of the prior art. To do this, the invention firstly relates to a deployable finned grid for an aircraft turbomachine thrust reversal system, the gate being capable of adopting a rest position and an active deployed position. wherein the vanes are further apart axially from each other than in the home position. According to the invention, the grid comprises, at least between two fins, elastic return means forcing said two fins to move axially from one another. Also, the invention advantageously makes it possible to improve the reliability of deployment of the grid, thanks to the presence of elastic return means forcing the fins to move apart from each other. The invention has at least one of the following optional features, taken alone or in combination. The grid comprises a plurality of axial elements for supporting and guiding the fins, each of the axial support and guide elements passing through an axial row of orifices respectively through the fins of the grid, the orifices of the same row with the same passage section. In addition, each axial support and guide element, at least in a running part thereof, traverses the associated row of orifices and is defined between the most upstream fin and the finest downstream vane. gate in the deployed active position, has an outer surface of constant cross section. This preferred solution allows the vanes to expand by sliding on the axial support and guide elements, for example rods, the outer surface of which remains uniform at least in the predefined running portion. It therefore contrasts with the solution of document FR 2,588,312, which requires telescopic support and guide elements, as can be seen in FIG. 6 of this document. Deployable support and guide elements are provided, the section of which increases with each fin going downstream, which contrasts with the constant section of the elements provided in the preferential solution of the invention. This results in a gain in terms of size, mass, and aerodynamic performance of the grid. Preferably, the elastic return means are arranged around one or more of axial elements for supporting and guiding the fins. Preferably, the elastic return means are arranged between each fin of the grid, and a fin directly consecutive within this grid. In addition, said elastic return means are configured so that in the deployed active position of the grid, the forces exerted by said elastic means on the fins, cause them to be regularly spaced axially from each other. Preferably, the elastic return means are made using spiral compression springs, and / or using one or more spring washers. The invention also relates to a thrust reversing system for an aircraft turbomachine, comprising a fixed element, a movable nacelle hood element and at least one deployable grid as described above. Preferably, the thrust reverser system comprises at least a first jack and stop means retaining axially downstream a downstream end of said gate, the system being designed so that the gate is deployed from its position. resting in its active position deployed thanks to the restoring force developed by said elastic return means, following an axial displacement downstream of the stop means, generated by a deployment of said first cylinder. In addition, said abutment means are preferably integral with said first cylinder.
    [0003] Alternatively, these abutment means could be independent of the first cylinder, for example provided integral with the movable element of nacelle hood. Preferably, the system also comprises at least a second cylinder connecting said fixed element of the system to the movable nacelle cowl element, so as to allow axial movement of the latter relative to the grid in its deployed active position. Preferably, the first and second cylinders respectively comprise a first cylinder rod and a second cylinder rod arranged concentrically.
    [0004] Finally, the subject of the invention is an aircraft turbomachine, preferably a turbofan engine, comprising a thrust reverser system as described above. Other advantages and features of the invention will become apparent in the detailed non-limiting description below.
    [0005] BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood on reading the detailed description which follows, non-limiting examples of implementation thereof, as well as the examination of the appended drawings among which; FIG. 1 represents a schematic view in longitudinal section of a turbojet according to the invention; FIG. 2 represents a more detailed view, in longitudinal half-section, of the thrust reversal system fitted to the turbojet engine of the preceding figure; FIG. 3 represents a more detailed view, in longitudinal half-section, of a deployable gate forming an integral part of the thrust reversal system shown in the previous figure; FIG. 4 and FIG. 5 show longitudinal half-section views of the thrust reversal system of FIG. 2, in different positions during its deployment; FIG. 6 is a partial perspective view of the thrust reversal system, in the same operating state as that of FIG. 5; - Figure 7 is a broader perspective view of the thrust reversal system, still in the same operating state as that of Figure 5; FIG. 8 represents a partial exploded view in perspective of the thrust reversal system shown in the preceding figures; - Figures 9 to 11 show partial perspective views of a portion of the thrust reversal system, in different positions during its deployment; and Figures 12 to 14 show half-sectional views of a thrust reversal system in different positions during deployment, the system being in the form of another preferred embodiment of the invention. 'invention. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS With reference to FIG. 1, a turbojet engine 1 is shown according to a preferred embodiment of the invention. It is a turbofan engine of longitudinal axis A, comprising a central motor 8, a primary flow 16 passing through a primary vein 12, a secondary flow 17 which passes through a fan 11 before passing into a secondary vein 13, and a nacelle 10. The primary and secondary streams are separated by a shroud 31 of the primary nozzle. The outer wall of this fairing is the inner wall 21 of the secondary stream 13. The nacelle 10 comprises downstream of the fan 11, in relation to a main direction 4 of gas flow within the turbojet, an inversion system 6 which is specific to the present invention and will be described in detail with reference to the following figures. In known manner, when the thrust reverser system is in the idle rest position and the turbojet engine performs its normal propulsion function, the two flows 16, 17 are ejected around a central exhaust cone 28 3027065 6 turbojet, by their respective veins 12, 13. This configuration is shown schematically on the half-section of the bottom of Figure 1. In contrast, when the thrust reversal function is required, a mobile nacelle hood member 30 is moved downstream, so as to move away from a fixed nacelle element 15. The downstream movement of the movable member 30 reveals expanded thrust reversal gates 32, as has been schematized on the half-section of the top of FIG. 1. During this phase of thrust reversal, movable flaps 20 are actuated so as to partially close the secondary vein 13 at the downstream end thereof, so that the seconda flow 17 is forced to escape by the grids 32. As it passes through the grids, the secondary flow is deflected so as to be reoriented upstream, thereby creating a braking force on the aircraft. Referring now to Figures 2 and 3, there will be detailed the thrust reversal system 6 shown in an idle rest state, as adopted when the turbojet performs its normal function of propulsion in flight. Overall, the system 6 comprises the fixed element 15, the movable nacelle hood member 30, as well as one or more deployable thrust reversal grilles 32. More specifically, the fixed element 15 constitutes the upstream portion of the inversion system 6. It essentially comprises a structural frame 34 centered on the axis of the turbojet, and an aerodynamic fairing element 36 forming an integral part of the nacelle, this element 36 being supported by the frame 34. movable member 30 has meanwhile a longitudinal half-section of hollow form, open axially upstream, for example overall V coated form. The interior space defined by the V is dedicated to the arrangement of the deployable grids 32, when in the rest position as shown in FIGS. 2 and 3. The inner surface 40 of the movable member 30 forms the delimitation external radial of the secondary vein 13, while its outer surface 42 is in the aerodynamic continuity of the aerodynamic fairing 36, located further upstream. The movable element 30 extends over 360 ° around the axis of the turbojet engine. The grids 32 also extend over 360 °, for example being arranged end-to-end in the circumferential direction. Alternatively, it could be a single grid 3027065 7 extending in one piece over 360 °. For the sake of clarity of the description, it will subsequently be considered that the thrust reversal system 6 has only one single grid extending over 360 °, it being understood, however, that the technical characteristics of the The invention applies analogously to the other case, in which several grids are provided and arranged end to end. The gate 32 thus has a deployable character in the axial direction. It is also called stretch grid or expandable grid. It is designed to be able to deploy axially so as to move from a rest position as shown in Figures 2 and 3, to an activated position deployed which will be described later. The gate 32 comprises several fins 44 successively arranged one behind the other in the axial direction, each of them being arranged in a transverse plane of the turbojet. Each of these fins 44 performs an air deflector function, in a manner known to those skilled in the art. In addition, maintaining the fins 44 between them is provided by a plurality of radial support and guide elements, only one of which is visible in FIGS. 2 and 3. This is a first rod 46. a first cylinder 48, whose cylinder 50 is integral with the frame 34. The rod 46, integral with the piston of the cylinder 48, passes through an axial row 54a orifices 52a formed through the fins 44. These orifices 52a all have the 20 same passage section, that is to say that they all here have the same diameter. This diameter is substantially identical to that of the running portion 46 'of the rod 46, the current portion being able to be defined as that passing through the row 54a of orifices 52a, being situated between the finest 44 in the grid, and the finest downstream. Nevertheless, the diameter of the rod 46 is preferentially uniform all along the latter, even beyond its current portion 46 ', until it is fastened to the piston (not visible in FIGS. 2 and 3). . The finest 44, the leftmost blade in FIG. 3, is integral with the frame 34 and slidably mounted on the rod 46. The other fins 44 are also slidably mounted on the rod 46, but not secured to the frame 34 and therefore able to move along the first rod 46.
    [0006] At its downstream end, the rod 46 carries one or more nuts 54 forming an abutment axially retaining, downstream, the fin 44 downstream of the grid 32. The nuts 54 are thus considered to be an integral part here. of the first jack 48, since they are integrally mounted on the jack rod 46.
    [0007] One of the peculiarities of the invention lies in the introduction of springs 56 between the fins 44, so as to force them to deviate axially from each other. The springs 56, of the spiral compression spring type, are arranged around the rod 46. More specifically, they are arranged around axial jackets 58 provided on the fins, these jackets defining the orifices 52a and being themselves arranged around The inner diameter of the springs thus corresponds substantially to the outer diameter of the liners 58. Preferably, on the rod 46, a single spring 56 is provided between two fins 44 directly consecutive axially, the two ends of the spring then being respectively in support against the two flanks opposite the fins concerned.
    [0008] More specifically, a spring 56 is provided between the uppermost fin and the second fin of the gate, another spring 56 is arranged between the second and third wings, and so on until the fin downstream of the grid 32. In the state shown in Figure 3, the cylinder rod 46 is in the retracted position. The fins 44 are kept close together, being sandwiched between the upstream fixed wing 44 and the nuts 54. In this state, the jack 48 in the retracted state is opposed to the restoring forces developed. by the springs 56, which are compressed. In this state where the gate 32 occupies a rest position not deployed axially, the fins 44 are in contact with each other, via their axial jackets 58. As will be detailed below, the output of the first cylinder rod 46 Consequently, the nuts 54 of the fixed wing 44 are pulled axially upstream, and thus allow the other fins 44 of the grid to move away from one another under the effect of the return force. springs 56 which relax. This makes it possible to constitute a reliable and clever technical solution, ensuring the deployment of the thrust reversal grill 32. It is noted that this deployment is also favored by the aerodynamic forces applying to the fins of the grid in progress. stretching, crossed by the secondary air flow. The thrust reverser system 6 is also equipped with a second jack 60, having a second jack rod 62 and a cylinder 64 secured to the frame 34, and placed at the rear of the cylinder 50 of the first jack 48. The cylinder rod 62 is movably and concentrically mounted inside the first cylinder rod 46. This second rod 62 extends downstream beyond the first rod 46, and extends towards the first rod 46. upstream by concentrically traversing the cylinder 50 of the first jack 48, as shown schematically in FIG. 3. The downstream end of the second jack rod 62 is mounted on a fitting 66 of the movable member 30, so as to connect this element 30 to the fixed element 15 of the system 6, and so as to control the axial spacing between these two elements 15, 30. As indicated previously, in the idle state of rest of the thrust reversal system 6 this axial spacing is zero since the two elements 15, 30 are arranged in continuity of one another.
    [0009] Referring now to FIGS. 4 and 5, there is shown the thrust reverser system 6 in different positions during its deployment, ie when it passes from the idle rest position previously described. at an active position to provide the thrust reversal function. Firstly, the two jack rods 46, 62 are simultaneously output by control of the cylinders 48, 60. The output of the second rod 62 causes the downstream withdrawal of the movable member 30, relative to the part fixed 15 of the system. At the same time, the output of the first jack rod 46 has the effect of displacing axially downstream the thrust nuts 54. This allows the fins 44 of the grid 32 to deviate axially from each other In other words, as the cylinder rod 46 leaves its cylinder 50, the grid unfolds progressively under the effect of the springs 56. which relax and push the fins 44 to be evenly distributed between the upstream fixed wing, and the nuts 54 in motion. FIG. 4 shows the gate 32 in its deployed active position, in which the jack rod 46 is maximally exposed with respect to the conditions of operation of the first jack 48. Due to the identity of the springs 56 between the fins 44 these are in fact spaced axially regularly from each other, or almost regularly. Indeed, even if a slight aerodynamic distortion is present in the secondary air flow passing through the gate, the differential of aerodynamic loads induced by this distortion on the succession of fins is generally negligible compared to the restoring force of the springs. . The spacing variations between the fins in the deployed active position of the grid are therefore very small. More generally, it is noted that the choice of the stiffness and the number of springs allows the control of the spacings between the fins, these spacings can then be intentionally irregular, being fixed at different values depending on the position of the springs. fins on the grid. When the gate 32 reaches its deployed active position of Figures 4 and 5, the output of the rod 46 is stopped, while the output of the other rod 62 is continued so as to continue the downstream movement of the element 30, relative to the grid 32. This makes it possible to fully discover the gate 32, and thus to reach the operational position of the thrust reversal system 6, as shown in FIG. 5. In this position, the secondary flow 17 flowing in the vein 13 is forced to pass through the gate 32, so as to reverse the flow direction and cause the desired braking. After its deflection by the gate 32, the stream 17 escapes upstream in the direction opposite to the direction 4, by borrowing the space released axially between the two elements 15, 30 of the thrust reversal system 6 The grid 32 is preferably equipped with several axial elements for supporting and guiding the fins 44, circumferentially spaced apart from one another. First of all, as shown schematically in FIG. 7, several assemblies 70 may be provided, each integrating a first jack 48 and a second jack 60. The jack rod 46 of each of these sets 70 then serves the purpose of axial element for supporting and guiding fins 44. As an example, the sets 70 may be circumferentially spaced from each other by an angle between 10 and 40 °. All or some of them only can be equipped with springs 3027065 11 54 for the deployment of the grid 32. These sets 70 are of course controlled simultaneously by conventional means, not described. To reinforce the holding and axial guidance of the fins 44, other means can be used, such as tracking rods 72. These rods 72 5 are similar to the cylinder rods 46, in particular in that they are each slidably arranged through a cylinder 74 fixed to the frame 34. The difference with the cylinder rods 46 is that they only follow the movement applied by these rods 46, that is to say that they are not controlled. They also traverse axial rows of orifices made through the fins, preferably also being surrounded by springs 54, aimed at the deployment of the grid. In this regard, with reference to FIG. 8, it is noted that each follower rod 72 passes through an axial row 54b of orifices 52b made through the fins 44. These orifices 52b all have the same passage section, that is, that is to say that they all have the same diameter, preferably identical to the diameter of the orifices 52a 15 associated with the piston rods 46. This diameter is therefore substantially identical to that of the running portion 72 'of the follower rod 72, the part current that can be defined identically is that adopted for the cylinder rods 46. The support and guide means of the fins 44 are therefore constituted by parallel axial rods 46, 72 on which these fins 20 can slide, and which at less the current portion 46 ', 72' has an outer surface of constant section, possibly different depending on the rods. Consequently, telescopic support and guidance axial elements are preferentially excluded because they generate congestion, mass, and drag problems at the gate.
    [0010] FIGS. 9 to 11 show a part of the gate 32, in different states during the activation of the thrust reverser system 6. This part of the grid which has been shown in these figures incorporates an assembly 70, as well as a follower rod 72. The operation and behavior of the other sets 70 and rods 72 are the same as those to be described below, for the elements shown.
    [0011] 3027065 12 The deployment of the gate 32 is effected by the output of the cylinder rod 46 of the assembly 70, as described above. During this exit, the downstream fin 44 presses axially downstream on abutment nuts 78, screwed to the end of the follower rod 72. This causes the follower rod to move downstream. 72, displacement which is carried out simultaneously with that of the rod 46. The instant at which the rod 46 is fully extended also corresponding to the moment when the follower rod 72 comes into abutment on the cylinder 74, at one end upstream of greater diameter. As a result, in the extended position of FIG. 10, the grid 32 is retained axially downstream not only by the nuts 54 of the cylinder rods 46, but also by the nuts 78 of the follower rods 72, abutting in their cylinders. After obtaining the deployed active position of the gate 32, the output of the jack rod 62 is continued as previously described, and diagrammed again in FIG. 11. Referring now to FIGS. 12 to 14, Another preferred embodiment is shown in which the follower rod principle 72 is retained. The change from the preferred embodiment described above lies in the simplification of the assemblies 70, which are only equipped with the jack 60, but more equipped with the jack 48. In this mode, the jack rod 62 thus always connects the movable member. 30 to the frame 34, via the cylinder cylinder 64 fixed to this frame of the fixed element 15. The cylinder rod 62 then passes with the clearance holes (not shown) formed through the fins 44 grids, without filling with function of support and axial guidance of the fins. This function is here ensured only by the follower rods 72, which are also the only ones to support the springs 56 for deploying the gate 32. In the idle rest state of the thrust reverser system 6 shown in FIG. 12 , the fin 44 the furthest downstream of the compacted grid 32 is retained by abutment means 80, integral with the movable element 3. It may for example be one or more fittings fixedly mounted on the movable hood 30 , preferably inside the V. The output of the cylinder rod 62 has the effect of axially spreading these stop means 80 of the fixed fin 44 the upstream. This allows the other fins 30 of the grid to move away from each other under the effect of the restoring force of the springs 56 surrounding the follower rods 72, and still forcing the finest downstream vane against the Stop 80. Also, in this embodiment, the deployment phase of the gate 32 is controlled by the jack 60, which thus fulfills the role of the first jack 48 implemented in the previous mode. Once the gate 32 has been fully deployed as shown in FIG. 13, the output of the jack rod 62 is continued to translate the movable element 30 downstream, and to fully discover the gate 32, as shown on FIG. FIG. 14. During this final phase as well as during the entire thrust reversal phase, the downstream grid is no longer maintained by the abutment means 80, which are then at a distance, but assured only by the nuts 78 of the follower rods 72, abutting in their respective cylinders 74. Whatever the embodiment, it is noted that the opposite action, aimed at making the reversal system 6 inactive, is carried out in operating the same steps as those described above, but in reverse chronological order. Of course, various modifications may be made by those skilled in the art to the invention which has just been described, solely by way of non-limiting examples. 20
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Deployable grid (32) with wings (44) for an aircraft engine turbomachine thrust reversal system (6), the grid being able to adopt a rest position and an active deployed position in which the fins (44) ) are further spaced axially from each other than in the rest position, characterized in that it comprises, at least between two fins (44), elastic return means (56) forcing said two fins (44) to s axially move away from each other.
    [0002]
    2. Grid according to claim 1, characterized in that it comprises a plurality of axial elements (46, 72) for supporting and guiding the fins (44), each of the axial support and guiding elements passing through an axial row. (54a, 54b) orifices (52a, 52b) formed respectively through the fins of the grid, the orifices (52a, 52b) of the same row (54a, 54b) having the same passage section, and in that each axial supporting and guiding element (46, 72), at least in a running part (46 ', 72') thereof passing through the associated row of orifices (54a, 54b) and being defined between the most upstream fin and the finest downstream of the grid (32) in the deployed active position, has an outer surface of constant cross section.
    [0003]
    3. Grid according to claim 2, characterized in that the elastic return means (56) are arranged around one or more of axial elements (46, 72) for supporting and guiding the fins (44).
    [0004]
    4. Grid according to any one of the preceding claims, characterized in that elastic return means (56) are arranged between each fin (44) of the grid (32), and a fin (44) directly consecutive within this grid, and in that said elastic return means (56) are configured so that in the deployed active position of the grid (32), the forces exerted by said elastic means 3027065 (56) on the fins (44) ), cause them to be regularly spaced axially from each other.
    [0005]
    5. Grid according to any one of the preceding claims, characterized in that the elastic return means are made using spiral compression springs (56), and / or using one or more elastic washers.
    [0006]
    6. Thrust reversing system (6) for an aircraft turbomachine (1), the system comprising a fixed element (15), a movable nacelle hood element (30) and at least one deployable grid (32) according to any one of the preceding claims.
    [0007]
    7. thrust reversal system according to claim 6, characterized in that it comprises at least a first cylinder (48) and stop means (54) 15 retaining axially downstream a downstream end of said grid (32), and in that the system is designed so that the grid deploys from its rest position to its deployed active position by virtue of the restoring force developed by said elastic return means (56), following a displacement axial downstream of the abutment means (54), generated by a deployment of said first cylinder (48), said abutment means (54) preferably being integral with said first cylinder (48).
    [0008]
    8. A thrust reverser system according to claim 6 or claim 7, characterized in that it also comprises at least a second jack (60) connecting said fixed element (15) of the system to the movable bonnet member. nacelle (30), 25 so as to allow axial movement of the latter relative to the grid (32) in its deployed active position.
    [0009]
    The thrust reverser system of claim 8, characterized in that the first and second cylinders (48, 60) each have a first cylinder rod (46) and a second cylinder rod (62) arranged concentrically. 3027065 16
    [0010]
    10. An aircraft turbomachine (1) comprising a thrust reverser system (6) according to any one of claims 6 to 9.
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    同族专利:
    公开号 | 公开日
    WO2016059331A1|2016-04-21|
    US20170370325A1|2017-12-28|
    US10378481B2|2019-08-13|
    GB2545599B|2020-08-12|
    GB2545599A|2017-06-21|
    FR3027065B1|2016-12-23|
    GB201705323D0|2017-05-17|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2588312A1|1985-10-08|1987-04-10|Rolls Royce|PUSH INVERTER FOR A GAS TURBINE ENGINE|
    FR2947869A1|2009-07-10|2011-01-14|Snecma|Grid for thrust reverser system of ducted-fan turbine engine i.e. jet engine, of aircraft, has two modules for respectively holding two opposite vanes at two ends of two supports, where grid is telescopic and extensible|US11131270B2|2017-12-21|2021-09-28|Safran Aircraft Engines|Turbojet equipped with a double-action actuator, which can be used to control reverse thrust|US3344604A|1965-12-14|1967-10-03|Gen Dynamics Corp|Apparatus for selectively reversing the thrust of front fan jet engines|US20180045140A1|2016-08-09|2018-02-15|Rolls-Royce Plc|Aircraft gas turbine engine nacelle|
    FR3062637B1|2017-02-07|2020-07-10|Airbus Operations |TURBOREACTOR NACELLE HAVING A DRIVE INVERTER DRIVE MECHANISM|
    US10995699B2|2018-02-19|2021-05-04|Mra Systems, Llc.|Thrust reverser cascade|
    FR3095676B1|2019-05-03|2021-04-09|Safran Aircraft Engines|Thrust reverser grille including acoustic treatment|
    US10995701B2|2019-09-05|2021-05-04|Rohr, Inc.|Translating sleeve thrust reverser assembly|
    法律状态:
    2015-10-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-15| PLSC| Search report ready|Effective date: 20160415 |
    2016-10-03| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 8 |
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    申请号 | 申请日 | 专利标题
    FR1459801A|FR3027065B1|2014-10-13|2014-10-13|DEPLOYABLE GRID WITH FINS FOR AN AIRCRAFT TURBOMACHINE PUSH INVERSION SYSTEM|FR1459801A| FR3027065B1|2014-10-13|2014-10-13|DEPLOYABLE GRID WITH FINS FOR AN AIRCRAFT TURBOMACHINE PUSH INVERSION SYSTEM|
    GB1705323.2A| GB2545599B|2014-10-13|2015-10-12|Deployable grille with fins for aircraft turbine engine thrust-reversal system|
    PCT/FR2015/052732| WO2016059331A1|2014-10-13|2015-10-12|Deployable grille with fins for aircraft turbine engine thrust-reversal system|
    US15/516,938| US10378481B2|2014-10-13|2015-10-12|Deployable grille with fins for aircraft turbine engine thrust-reversal system|
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