• 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:
    A method of manufacturing a gate for a thrust reverser of a turbomachine, said grid comprising a frame inside which are arranged several rows of fins, the method comprising the steps of making said fins by stamping a composite material to thermoplastic matrix, and weld said fins together or said frame by induction welding.
    公开号:FR3048025A1
    申请号:FR1651372
    申请日:2016-02-19
    公开日:2017-08-25
    发明作者:Wouter Balk；Bertrand Desjoyeaux
    申请人:Safran SA；
    IPC主号:
    专利说明:

    Method of manufacturing a gate for turbomachine thrust reverser
    TECHNICAL AREA
    The present invention relates to a method of manufacturing a gate for an aircraft turbomachine thrust reverser, as well as the gate obtained by this method.
    STATE OF THE ART The state of the art includes the document FR-A1-2 978 991 which relates to a sliding gate thrust reverser.
    Figures 1 and 2 show an aircraft turbine engine 1. Such a turbomachine 1 conventionally comprises an air inlet 11 comprising a fan 2 whose outlet air flow is divided into a flow of air which enters the engine 4 and forms a hot flow or primary flow P, and a flow of air flowing around the engine 4 and inside a nacelle 10, and which forms a cold flow or secondary flow S.
    The engine 4 typically comprises from upstream to downstream, in the direction of flow of the gases, at least one compressor, a combustion chamber, at least one turbine, and an exhaust nozzle 5 in which the combustion gases are ejected. .
    The primary air flow P is compressed in the compressor, burned in the combustion chamber and then expanded in the turbine which drives the rotors of the compressor and the fan 2. The primary flow P is ejected into the nozzle 5 along an ejection cone 6.
    The secondary flow S downstream of the fan 2 passes through the arms of an intermediate casing 22 and possibly guide vanes and is ejected directly into the atmosphere, along an outer casing 14 of the motor. The nacelle 10 surrounds a fan casing 21 and the intermediate casing 22. The nacelle 10 is formed downstream of the air inlet 11 of a first fairing element 12 which extends along the fan casing 21 and of an outer shell of the intermediate casing 22. Downstream of the intermediate casing 22, the nacelle 10 comprises a second fairing element 13 which defines a discharge nozzle of the secondary flow S.
    The turbomachine is equipped with a thrust reverser by which the secondary flow S can be deflected radially and upstream so as to cancel the thrust and provide a reverse thrust braking of the aircraft, for example when traveling at ground.
    There are different types of thrust reversers. FIG. 3 shows a thrust reverser comprising a downstream secondary flow nozzle element while deploying flow reversing flaps and opening a passage along the nacelle through which the flow blocked by the reversing flaps is radially deflected. towards the outside of the engine. At least one gate is disposed in the passageway to guide the deflected flow.
    Figure 3 shows the thrust reverser in the active position. The inverter comprises at least one grid 15 movable along the inner wall of the first fairing element 12, between a position where it is entirely retracted inside this first element 12 and the active position shown in the figure. The grid 15 comprises radial fins, curved upstream, parallel to each other and spaced from each other. Their function is to guide the flow through the grid radially and upstream.
    A space 12A is provided between the ferrule 221 of the intermediate casing and the fairing element 12 to house the organs of the thrust reverser. The transverse wall connecting the first element 12 to the shell 221 delimits the upstream edge of the radial opening in the nacelle and forms the deflection edge 121 of the flow.
    This space also contains actuators 19 actuating the inverter; it can be cylinders. The gate 15 is guided in its movement from upstream to downstream by a plurality of guide rails 122. These rails extend from the deflection edge 121 parallel to the axis of the nacelle. The length of these rails corresponds to the maximum deployment distance of the grid. The grid comprises, for example, slides that rest on the rails along its movement.
    The grid 15 comprises a plurality of radial fittings 151 at the end of which a synchronization ring 16 is fixed. This ring is perpendicular to the axis of the nacelle. The ring is connected to piston rods of the driving members 19.
    On these fittings 151 or on the synchronization ring are mounted and articulated inverter flaps 17. The flaps may comprise clevises traversed by axes perpendicular to the axis of the nacelle, which also pass through the fittings. Thus, the flaps can pivot about the axes of the fittings 151 of grids 15.
    The second fairing element 13 is fixed to the grid 15. Thus, when the grid moves in translation, it carries with it the inverting flaps 17 and the second fairing element 13. This element 13 comprises an outer wall 131 and a wall internal 132. These two walls meet downstream to form the downstream edge of the nacelle.
    The grid 15 of a thrust reverser is generally formed of sectors most often made of composite material or aluminum foundry. The disadvantage of grids composite material is related to their high cost, which is generated mainly by the manufacturing process which is laborious and requires a lot of manual intervention.
    The cells inside the grid (between the fins) are strongly curved and therefore can not be obtained by demolding. The current manufacturing process consists of draping pre-impregnated carbon fabrics around silicone-shaped counter-molds in the shape of the cell. After baking the resin, the silicone molds are removed. The disadvantage of silicone molds is their short life because it is necessary to replace them after a few dozens of cycles. The object of the present invention is to provide a process for manufacturing grids made of composite material, which is compatible with high speeds, which is more cost-competitive due to an increased automation potential and more regular quality.
    SUMMARY OF THE INVENTION The invention proposes a method of manufacturing a turbine engine thrust reverser grid, this grid comprising a frame inside which are arranged several rows of fins, the method comprising the steps of: - Making said fins by stamping a thermoplastic matrix composite material, and - welding said fins together or said frame by induction welding. The invention proposes to manufacture the grid by two techniques namely one by a stamping technique by means of a press for example (equipped with a tool punch-matrix) for the realization of the fins, and other a welding technique here by induction. The material used for the manufacture of the grid is a thermoplastic matrix composite material which is compatible with the abovementioned techniques.
    For induction welding, the technique described in US-A1-2010 / 0206469A1 can be used. This technique melts the thermoplastic matrix through eddy currents generated in the fibers of the reinforcement. The advantage of induction welding lies in the fact that there is no supply of foreign matter. As long as the process is automatized and made repeatable, it is possible to certify a welded joint as a primary stress path, which is not the case with a glued joint. The invention applies to any type of grid, sliding, fixed, etc.
    The method according to the invention may comprise one or more of the following features, taken separately from each other or in combination with each other: - each fin or a series of fins is formed by stamping an elongated plate after stamping, said plate has a shape substantially Z, U, Ω, or forms zigzags or corrugations, - said plate comprises a fibrous reinforcement and a thermoplastic matrix, - the stamping is preceded by a heating step of said plate, for example in an infrared oven, - after stamping, said plate is welded to another stamped plate and / or to a spar for separating two adjacent rows of fins, - after stamping, said plate comprises at least one first portion having an aerodynamic profile and defining a fin, and two second flat welding portions disposed on either side of said first portion. The invention also relates to a gate for a thrust reverser of a turbomachine, obtained by a method as described above.
    Advantageously, each of said fins is formed in one piece with flat end portions of welding. The invention also relates to an aircraft turbomachine, comprising at least one grid, possibly sectored, as described above.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: Figure 1 is a schematic view of an aircraft turbine engine; FIG. 2 is a schematic half-view in axial section of the turbomachine of FIG. 1; - Figure 3 is a schematic sectional and perspective view of a thrust reverser of the turbomachine of Figure 1, here in the active position; FIG. 4 is a block diagram showing steps of the method according to the invention; FIG. 5 is a schematic perspective view of a plate used in the process according to the invention; - Figure 6 is a schematic perspective view of a fin obtained by stamping the plate of Figure 5; - Figure 7 is a schematic perspective view of a grid in the process of manufacture and having welded fins of the type of that of Figure 6; - Figure 8 is a schematic perspective view of fins obtained by stamping a plate similar to that of Figure 5; FIG. 9 is a schematic perspective view of a grid during manufacture and comprising welded fins of the type of those of FIG. 8; - Figure 10 is a schematic perspective view of fins obtained by stamping a plate similar to that of Figure 6; FIGS. 11 to 13 are diagrammatic perspective views of a grid during manufacture and comprising welded fins of the type of those of FIG. 10.
    DETAILED DESCRIPTION
    The detailed description that follows provides several embodiments of a method of manufacturing a gate of a turbomachine thrust reverser, this method being illustrated schematically in FIG.
    The grid that can be obtained by the manufacturing method is of the type described above, in particular with reference to FIG. 3. It essentially comprises a frame inside which are arranged several rows of fins.
    The method can be used to manufacture a complete grid or a grid sector, this grid or grid sector having a generally parallelepipedal or curved shape. In the case for example where the thrust reverser comprises grids or grid sectors 360 °, each grid or grid sector may have a curved shape and extend over an angular sector of a few tens of degrees for example.
    As illustrated in FIG. 1, the process essentially comprises two steps: a first step 200 for producing the fins of the grid by stamping a thermoplastic matrix composite material, and a second welding step 300. fins between them or even the frame of the grid, by induction welding.
    Figures 5 and following illustrate three embodiments of the invention.
    Figures 5 to 7 show a first embodiment of the invention wherein the fins 402 are made by stamping independently of each other.
    FIG. 6 shows a preform 400 comprising a fin 402 after the embossing operation, and FIG. 5 represents a plate 404 which is used for producing this preform 400.
    The plate 404 has an elongated substantially parallelepiped shape. It has a relatively small thickness to facilitate the stamping operation. In the present case, this plate is made of a thermoplastic matrix composite material. More specifically, it comprises a fibrous reinforcement embedded in a thermoplastic matrix.
    The fibrous reinforcement is for example formed from carbon fibers or glass. The thermoplastic matrix is for example formed from polymers such as PEI, PPS, PEEK PEKK, PA.
    In a manner known to those skilled in the art, the stamping is carried out by means of a press which is equipped with punch-die tooling. The plate 402 is intended to be interposed between the punch and the matrix of the tool and to be pressed between these elements to impose a plastic deformation.
    This deformation can be enabled / facilitated by heating the plate 404. The plate is for example heated to a predetermined temperature, for example in an infrared oven, before its stamping.
    Advantageously, the heating of the plate makes it possible to heat the thermoplastic matrix beyond its melting point. In the above example where the thermoplastic matrix is PEEK, the plate is preferably heated to a temperature of 380 ° C with its stamping.
    The plate 404 comprises adjacent portions, separated schematically by dashed lines in FIG. 5. These portions are intended to form three distinct portions of the preform 400 after stamping. The preform comprises a median portion 406 intended to form the fin 402, and, on either side of this median portion 406, two end portions 408 of welding.
    The median portion 406 has an aerodynamic profile. It has for example in cross section a curved shape. The portion 406 may have a concave curved surface forming a lower surface and a convex curved surface forming an upper surface.
    End portions 408 are planar and configured to be applied and welded to members 410 for separating two rows of adjacent fins from the grid (FIG. 7). FIG. 7 represents a grid in the course of manufacture, this grid comprising here two longitudinal members 410 and two rows of fins 402. It can be seen that the end portions 408 of a row of fins are applied and fixed by welding against one side of one of the longitudinal members 410, and that their opposite end portions are applied and fixed by welding against one face facing another of the longitudinal members 410.
    In the example shown, the fins are substantially parallel to each other and the longitudinal members are substantially parallel to each other.
    The first embodiment described in the foregoing uses substantially Z-shaped preforms. The advantage of this form lies in the simplicity of the stamping tooling (compaction angle of 45 ° with the flanks) and the possibility of to easily unmold the preform.
    In an alternative embodiment not shown, the preform could have a substantially U or W shape. It would then require more complex punching tooling with beveled wedges to allow the compacting of two flanks in parallel. There may be an aerodynamic advantage in U-shaped fins, because of the possibility of positioning the connecting radius between the sidewalls and the aerodynamic profile still on the domed side of the fin.
    Figures 8 and 9 show another embodiment of the invention wherein several fins 502 are made simultaneously during a stamping operation.
    Figure 8 shows a preform 500 having a series of fins 502 after the stamping operation. This preform is made from a plate similar to that of Figure 5 but which of course can be longer.
    The plate then comprises several adjacent portions which are intended to form several distinct portions of the preform 500 after stamping. The preform comprises portions 506 intended to form fins 502, and between two adjacent portions 506 and at each of the longitudinal ends of the preform, a welding portion 508.
    Each portion 506 has an aerodynamic profile similar to that of the portion 406 above.
    The portions 508 are planar and configured to be applied and welded directly to each other without a spar (FIG. 9). FIG. 9 represents a grid during manufacture, this grid comprising here several stamped preforms arranged next to one another to define several adjacent rows of fins. The preforms can be nested within each other as shown in the drawings.
    In the example shown, the fins are substantially parallel to each other and the portions 508 of the preforms are substantially parallel to each other and bear two by two at each of their ends.
    In this embodiment, the preform has a zigzag shape or steps. This approach allows a better continuity of the fibers and fewer parts to assemble since there is no spar.
    Figures 10 to 13 show another embodiment of the invention wherein several fins 602 are made simultaneously during a stamping operation.
    Figure 10 shows a preform 600 having a series of fins 602 after the stamping operation. This preform is made from a plate similar to that of Figure 5 but which of course can be longer.
    The plate then comprises several adjacent portions which are intended to form several distinct portions of the preform 600 after stamping. The preform comprises portions 606 intended to form fins 602, and, between two portions 606 adjacent and at each of the longitudinal ends of the preform, a welding portion 608.
    Each portion 606 has an aerodynamic profile similar to that of the portion 406 above.
    The portions 608 are planar and configured to be applied and welded directly to each other without a spar (FIGS. 11 and 12). Figures 11 and 12 show a grid in the process of manufacture, this grid here comprising several preforms stamped and arranged next to each other to define several adjacent rows of fins.
    In the example shown, first fins are substantially parallel to each other and the other fins are also parallel to each other but inclined relative to the first. The portions 608 of the preforms are substantially parallel to each other.
    The grid of FIG. 12 is then framed by profiles 610 which delimit the aforementioned frame, and which are also inductively welded to the preforms. The grid of FIG. 12 can then be used in an aircraft turbomachine, such as that represented in FIGS. 1 and 2.
    In this embodiment, the preform has a wavy shape. Contrary to the previous embodiments where the interchain cells have a generally rectangular cross-sectional shape, inter-alveolar cells here have a hexagonal cross section.
    The fact of developing the grids by welding from stamped parts made of thermoplastic resin brings several advantages: - elimination of the labor related to the draping of the prepregs, - reduction of the cooking cycle time, - possibility of increased automation of the process, - no need to store raw materials in the freezer, - more repeatable quality, - scrap material and scrap parts easier to recycle, and - more energy efficient and consumable process.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A method of manufacturing a gate for a thrust reverser of a turbomachine, said grid comprising a frame inside which are arranged several rows of fins (402), the method comprising the steps of: - producing said fins by stamping a thermoplastic matrix composite material, and - welding said fins together or said frame by induction welding.
    [2" id="c-fr-0002]
    2. Method according to the preceding claim, wherein each fin (402) or a series of fins is formed by stamping a plate (404) of elongated shape.
    [3" id="c-fr-0003]
    3. Method according to the preceding claim, wherein, after stamping, said plate (404) has a shape substantially Z, U, Ω, or forms zigzags or corrugations.
    [4" id="c-fr-0004]
    The method of claim 2 or 3, wherein said plate (404) comprises fibrous reinforcement and a thermoplastic matrix.
    [5" id="c-fr-0005]
    5. Method according to one of claims 2 to 4, wherein the stamping is preceded by a step of heating said plate.
    [6" id="c-fr-0006]
    6. A method according to one of claims 2 to 5, wherein, after stamping, said plate (404) is welded to another stamped plate and / or a spar (410) for separating two adjacent rows of fins.
    [7" id="c-fr-0007]
    7. Method according to one of claims 2 to 6, wherein, after stamping, said plate (404) comprises at least a first portion (406) having an aerodynamic profile and defining a fin, and two second planar portions (408). welding devices arranged on either side of said first portion.
    [8" id="c-fr-0008]
    8. Grid for turbomachine thrust reverser, obtained by a method according to one of the preceding claims.
    [9" id="c-fr-0009]
    9. Grid according to the preceding claim, wherein each of said fins (402) is formed integrally with flat end portions welding.
    [10" id="c-fr-0010]
    10. Aircraft turbomachine, comprising at least one grid, possibly sectored, according to claim 8 or 9.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3048025B1|2019-05-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2005110723A1|2004-04-27|2005-11-24|Aircelle|Method for production of elements such as thrust-reverser cascade vanes by moulding of a composite material|
    US20130333830A1|2011-08-08|2013-12-19|The Boeing Company|Flexible Compactor with Reinforcing Spine|
    EP2944452A2|2014-05-15|2015-11-18|The Boeing Company|Thermoformed cascades for jet engine thrust reversers|EP3527812A1|2018-02-19|2019-08-21|MRA Systems, LLC|Thrust reverser cascade|
    EP3599370A1|2018-07-25|2020-01-29|Rohr, Inc.|Low cost joined cascade|
    EP3623611A1|2018-09-14|2020-03-18|Rohr, Inc.|Thrust reverser cascade array and method for producing the same|
    EP3726038A1|2019-04-17|2020-10-21|Hutchinson|Method for manufacturing a grid for a thrust reverser|
    EP3736432A1|2019-05-06|2020-11-11|Rohr, Inc.|Forming a thrust reverser cascade using corrugated bodies|
    法律状态:
    2017-01-09| PLFP| Fee payment|Year of fee payment: 2 |
    2017-08-25| PLSC| Publication of the preliminary search report|Effective date: 20170825 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 3 |
    2019-01-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 6 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1651372|2016-02-19|
    FR1651372A|FR3048025B1|2016-02-19|2016-02-19|METHOD FOR MANUFACTURING A TURBOMACHINE PUSH INVERTER SCALE|FR1651372A| FR3048025B1|2016-02-19|2016-02-19|METHOD FOR MANUFACTURING A TURBOMACHINE PUSH INVERTER SCALE|
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