• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention proposes an assembly (1) comprising: - a front cone (3) of a turbomachine, - a front ferrule (5) of a turbomachine, downstream of the cone with respect to an air flow in the turbomachine, - a seal sealing member (40) disposed between the front cone and the front ferrule, the assembly being characterized in that the front cone and the front ferrule each comprise a circumferential thread (33, 38), said threads (33, 38) being adapted to cooperate so as to allow mounting by screwing the front cone (3) on the front ferrule (5), the assembly ensuring a compression of the seal (40) between said front cone (3) and said ferrule before (5).
    公开号:FR3053430A1
    申请号:FR1656185
    申请日:2016-06-30
    公开日:2018-01-05
    发明作者:Guillaume Maurice Rene Patin；Alexis Thomas CHABOUD；Alexandre Michel Henri Hasquenoph
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    © Publication number: 3,053,430 (to be used only for reproduction orders)
    ©) National registration number: 16 56185 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE
    ©) Int Cl 8 : F16 J 15/02 (2017.01), F 16 J 15/46
    A1 PATENT APPLICATION
    ©) Date of filing: 30.06.16. ©) Applicant (s): SNECMA Société anonyme - FR. ©) Priority: ©) Inventor (s): PATIN GUILLAUME MAURICE RENE, CHABOUD ALEXIS THOMAS and HASQUENOPH (43) Date of public availability of the ALEXANDRE MICHEL HENRI. request: 05.01.18 Bulletin 18/01. ©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ©) Holder (s): SNECMA Société anonyme. related: ©) Extension request (s): ©) Agent (s): REGIMBEAU.
    FR 3 053 430 - A1
    TURBOMACHINE ASSEMBLY FOR A SEALED ASSEMBLY OF A FRONT CONE ON A FRONT ROD.
    The invention provides a set (1) comprising:,
    - a front cone (3) of a turbomachine,
    - a front shroud (5) of a turbomachine, downstream of the cone relative to an air flow in the turbomachine,
    a seal (40) disposed between the front cone and the front ferrule, the assembly being characterized in that the front cone and the front ferrule each comprise a circumferential thread (33, 38), said threads (33, 38) being adapted to cooperate so as to allow mounting by screwing the front cone (3) on the front ferrule (5), the mounting ensuring compression of the seal (40) between said front cone (3) and said front ferrule (5).


    i
    FIELD OF THE INVENTION
    The invention relates to a turbomachine assembly comprising a front cone, a front ferrule and a seal.
    STATE OF THE ART
    The front cone is a part of revolution, of conical shape, around an axis of the turbomachine. The front cone is located upstream of the fan of the turbomachine, relative to the direction of air flow in the turbomachine.
    The front ferrule is an annular part of revolution around the axis of the turbomachine, located immediately downstream of the front cone relative to the direction of air flow in the turbomachine.
    The front cone-ferrule assembly is integral with the fan, and is therefore integral with a rotary shaft of the turbomachine. This assembly makes it possible to orient the air flow towards the fan of the turbomachine.
    The connection between the front cone and the front shroud of the turbomachine is currently carried out by bolted connection.
    For this purpose, the front cone and the front ferrule are each provided with an annular flange serving as a support for the screwing. The flange of the front cone is located at the downstream end of said cone, relative to the direction of air flow in the turbomachine. The front ferrule flange is located at the upstream end of said ferrule, relative to the direction of air flow in the turbomachine. Each flange comprises two annular surfaces: a surface tangential to the axis of the turbomachine, that is to say extending circumferentially around the axis XX of the turbomachine, and a radial surface relative to the axis of the turbomachine.
    The flanges are adapted so that, during screwing, the tangential surfaces of the flanges of the cone and of the front ferrule are brought into contact with each other, and the same is true for the radial surfaces of the flanges of the cone and of the ferrule before them.
    FIG. 1 shows a view of an example of a front cone 2. In this example, it is provided that the screws are located axially with respect to the axis XX of the turbomachine. Therefore, they will be able to pass through each of the radial annular surfaces of the flange 11 of the front cone, and of the flange (not shown) of the front ferrule. To allow the establishment of the screws, notches 10 are formed circumferentially on the radially outer surface of the front cone. This assembly degrades the aerodynamic performance of the front cone, and therefore of the assembly formed by the cone and the ferrule.
    FIG. 2 represents another example of assembly of a front cone 3 on a front ferrule 5. The connection is made this time via screws 7 located radially with respect to the axis X-X of the turbomachine. Therefore, they each pass through the annular tangential surfaces 20, 22 of the flanges 30, 32 of the front cone 3 and of the front ferrule 5. The installation of the screws also requires making notches 9 on the radially external surface of the cone before, although these notches 9 degrade the aerodynamic performance of the cone less than that of the preceding example.
    However, screwing in the radial direction relative to the axis X-X of the turbomachine involves screwing tangential surfaces 20, 22 of the cone and the ferrule together. The seal between the cone and the ferrule is then no longer sufficient to prevent the flow of water at the cone ferrule interface which could infiltrate and cause early wear of the assembly, in particular by corrosion of the parts. To overcome the risk of infiltration, a seal could be integrated at the interface between the front cone and the front ferrule. However, in order to be effective, it should be compressed during assembly, which is not guaranteed with the current design.
    DESCRIPTION OF THE INVENTION
    One of the aims of the invention is to alleviate the drawbacks of the prior art, by proposing a solution for assembling a front cone and a front shroud of a turbomachine allowing good connection tightness, low disturbance of the flow. aerodynamics, a reduction in the overall mass of the parts, and a saving of time during assembly and / or maintenance of the assembly.
    In this regard, the subject of the invention is an assembly comprising: a front cone of a turbomachine, a front ferrule, downstream of the cone with respect to an air flow in the turbomachine, a seal placed between the front cone and the front ferrule, the assembly being characterized in that the front cone and the front ferrule each comprise a circumferential thread, said threads being adapted to cooperate so as to allow mounting by screwing the front cone onto the front ferrule, mounting ensuring compression of the seal between said front cone and said front ferrule.
    Advantageously, but optionally, the assembly according to the invention can also comprise at least one of the following characteristics:
    the cone and the front ferrule each comprise an assembly surface carrying a respective thread, said surface being a tangential annular surface centered on an axis of the turbomachine, the assembly surface of the front cone is radially internal to said cone, and in which the assembly surface of the front ferrule is radially external to said ferrule, the assembly surface of the front cone is radially external to said cone, and in which the assembly surface of the front ferrule is radially internal to said ferrule, each assembly surface of the cone and the ferrule comprises a guide surface adjacent to the respective circumferential thread, the guide surface is arranged upstream of the thread with respect to the direction of flow of the air in the turbomachine, the cone and the front ferrule comprise an annular surface radial with respect to the axis, said surfaces being adapted to come into contact with one another during screwing, so as to compress the annular seal disposed between said surfaces, the assembly further comprises a relative rotation stop system for the threads, the rotation stop system comprises a polymer ring mounted on an upstream end of a thread and / or a reversible adhesive, the front cone comprises a radially external surface comprising at least three support points of a clamping tool, said points being regularly distributed over the circumference of said surface, and each fulcrum is formed in hollow relative to the surface, being formed by one of the following group: notch, groove, or flat, of any shape, formed at the level of the radially external surface of the base of the front cone
    The invention also relates to a turbomachine, comprising an assembly according to the preceding description.
    The proposed solution of assembling the front cone to the front ferrule by a circumferential thread makes it possible to mount these two parts while compressing the seal extending between them, which ensures the tightness of the 'assembly. The thread is hidden after assembly, which does not disturb the aerodynamic flow. In addition, the invention eliminates the notches in the radially outer surfaces of the cones of the prior art for mounting the assembly screws. This allows better circulation of the aerodynamic flow around the front cone-ferrule assembly.
    Threading is a solution well suited for this type of connection vis-à-vis the mechanical stresses undergone by the cone-ferrule connection before. In fact, since the rotation of the blower is always in the same direction, it suffices to choose the appropriate thread direction so that the rotation of the blower tends to increase the tightening.
    Threading also has the advantage of facilitating the manufacture and maintenance of the assembly, thereby reducing its production and maintenance cost. Indeed, the set includes only two main parts, without connecting elements such as screws. Thus, in addition to reducing the overall mass of the assembly, the step of dismantling and reassembling the front cone during maintenance under the wing, typically when the aircraft is parked at the airport, is less tedious, shorter, and less prone to errors. In addition, the machining of circumferential threads is a manufacturing step known and mastered by those skilled in the art. The implementation of the invention at the industrial level therefore generates no additional cost and, even, withdraws costs linked to intervention times to remove and reassemble the connecting screws. Finally, the use of an adequate clamping tool preserves the paint with which the cone and ferrule are coated. In fact, the use of clamping screws in the prior art generally causes the paint to flake off.
    DESCRIPTION OF THE FIGURES
    Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and which should be read with reference to the appended drawings in which:
    FIG. 1, already described, represents a front cone of a turbomachine according to the prior art,
    FIG. 2, already described also, represents a sectional view of an example of assembly of a front cone on a front ferrule according to the prior art,
    FIG. 3 illustrates an example of an assembly comprising a cone and a front ferrule according to an embodiment of the invention,
    FIG. 4a is a sectional view of an embodiment of the respective flanges of the cone and of the front ferrule arranged before tightening,
    FIG. 4b is a sectional view of an embodiment of the respective flanges of the cone and of the front ferrule at the end of tightening.
    FIG. 5a is a sectional view of another embodiment of the respective flanges of the cone and of the front ferrule arranged before screwing. FIG. 5b is a sectional view of another embodiment of the respective flanges of the cone and of the front ferrule at the end of tightening.
    Figure 6 is a sectional view of another possible embodiment of the respective flanges of the cone and the front ferrule
    DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT OF THE INVENTION
    We will now describe at least one assembly 1 of a turbomachine according to one embodiment of the invention.
    The assembly 1 comprises a front cone 3, the front cone being a part of revolution about an axis X-X of the turbomachine, of conical shape. The assembly 1 further comprises a front ferrule 5, an annular part of revolution around the axis X-X of the turbomachine, located immediately downstream of the front cone relative to the direction of flow of the air in the turbomachine.
    The front cone-ferrule assembly is integral with the fan (not shown), downstream of this assembly, and is therefore integral with a rotary shaft (not shown) of the turbomachine. This assembly makes it possible to orient the air flow towards the fan of the turbomachine. In addition, the assembly includes a seal 40 disposed between the front cone and the front ferrule.
    We will describe in more detail the different components of the assembly.
    Front cone
    The front cone 3 comprises, at its downstream end, an annular flange 30 for assembly to the front ferrule 5 by screwing. This flange 30 comprises two distinct surfaces: a radial annular surface 31, and a tangential annular surface 32. With reference to FIGS. 4a, 4b, 5a and 5b, in a possible embodiment of the invention, the tangential annular surface 32 of the flange is located upstream of the radial annular surface 31 of the flange, relative to the direction of air flow in the turbomachine. Said tangential annular surface is then on a radially internal surface of the front cone. Referring to Figure 6, in another possible embodiment of the invention, the tangential annular surface 32 of the flange is located downstream of the radial annular surface 31 of the flange, relative to the direction of flow of the in the turbomachine. Said surface is then located on a radially external surface of the front cone.
    The annular flange 30 of the front cone 3 further comprises a circumferential thread 33 arranged on the tangential annular surface 32 of the flange 30. This circumferential thread allows mounting by screwing the front cone 3 on the front ferrule 5. The thread extends thus on a plurality of turns, preferably between 2 and 10 turns, for example on 4, 5 or 6 turns. In addition, the thread direction is chosen adequately, so that the rotation of the blower tends to increase the tightening.
    Advantageously, the tangential annular surface 32 of the flange 30 comprises a guide surface 34 adjacent to the circumferential thread 33. This guide surface is preferably a smooth surface, devoid of threads or roughness, and capable of coming into abutment against a complementary centering surface 39 of the front ferrule 5, described below, to allow the two parts to be centered with respect to each other. This guide surface can be located upstream, or downstream of said circumferential thread according to two possible embodiments of the invention. With reference to FIGS. 4a and 4b, the guide surface 34 can be located upstream from the thread 33.
    As a variant, with reference to FIGS. 5a and 5b, the guide surface 34 of the cone is located downstream of the thread 33.
    Front ferrule
    The front ferrule further comprises, at its upstream end, an annular flange 35 for assembly to the cone 3 by screwing. This flange 35 comprises two distinct surfaces: a radial annular surface 36, and a tangential annular surface 37. With reference to FIGS. 4a, 4b, 5a and 5b, in one possible embodiment of the invention, the annular tangential surface 37 of the flange is located upstream of the radial annular surface 36 of the flange, relative to the direction of air flow in the turbomachine. Said tangential annular surface is then located on a radially external surface of the front shell. Referring to Figure 6, in another possible embodiment of the invention, the tangential annular surface 37 of the flange is located downstream of the radial annular surface 36 of the flange, relative to the direction of flow of the in the turbomachine. Said tangential annular surface is then located on a radially internal surface of the front ferrule.
    The annular flange 35 of the front ferrule 5 further comprises a circumferential thread 38 arranged in the tangential annular surface 37 of the flange. This circumferential thread allows mounting by screwing the front cone 3 on the front ferrule 5, it is therefore suitable for cooperating with the thread 33 of the front cone. The thread 38 thus extends over a plurality of turns, preferably between 2 and 10 turns, for example over 4, 5 or 6 turns.
    Advantageously, the tangential annular surface 37 of the flange 35 comprises a guide surface 39 adjacent to the circumferential thread 38. This guide surface can be located upstream or downstream of said circumferential thread, according to the two embodiments shown respectively in the figures 4a and 4b on the one hand, and 5a and 5b on the other. With reference to FIGS. 4a and 4b, the guide surface 39 can be located upstream from the thread 38.
    As a variant, with reference to FIGS. 5a and 5b, the guide surface 39 of the ferrule is located downstream of the thread 38.
    Referring to Figures 4a, 4b, 5a 5b, and 6 the seal is an annular seal 40, disposed between the front cone 3 and the front ferrule 5. More specifically, the seal 40 is located between the respective radial annular surfaces 31, 36 of the respective flanges 30, 35 of the cone and of the front ferrule, where appropriate in respective grooves 42, 43 formed in said respective radial annular surfaces of said flanges.
    The screw cone mounting of the front cone 3 on the front ferrule 5 thus ensures compression of the seal 40 between the front cone 3 and the front ferrule 5. This compression of the seal ensures complete sealing of the junction between the front cone and the front ferrule. Indeed, the presence of the seal put under compression prevents the infiltration of liquid into the gap 41 formed by the contacting of the respective annular surfaces 31 and 36 of the respective flanges 30 and 35 of the cone and of the front ferrule .
    Stop in rotation
    The assembly 1 further comprises a system for stopping the relative rotation of the respective threads of the front cone and of the front ferrule.
    Advantageously, with reference to FIGS. 4a, 4b, 5a and 5b, the rotation stop system comprises a polymer ring 50. Said ring can be disposed in a circumferential groove 51 arranged in the flange 30 of the cone at the upstream end the circumferential thread 33 of the annular tangent surface 32 of the flange 30 of the front cone 3.
    As a variant, the ring 50 may be arranged in a circumferential groove arranged in the flange 35 of the ferrule, at the downstream end of the circumferential thread 38 of the tangential annular surface 37 of the flange 35 of the ferrule.
    At the end of the screwing, with reference to FIGS. 4b and 5b, the upstream end of the circumferential thread 38 of the tangential annular surface 37 of the flange 35 of the front ferrule 5, comes into contact with the ring 50 to deform it in its rigid housing 51. In a manner known per se, the deformation induced by bringing the thread 38 and the ring 50 into contact ensures, by friction, that the thread 38 is prevented from rotating with respect to the thread 33. The ring thus described is included as a wearing part capable of being exchanged as many times as necessary, after a certain cycle of assembly-disassembly.
    As a variant, the rotation stop system comprises a reversible adhesive, or "thread locker", the respective circumferential threads 33 and 38 of which are induced before screwing. By "reversible", the skilled person understands that it is a question of torque applied during rotation. Once the screwing is completed and the glue has dried, the unscrewing rotation is prevented over a range of unscrewing torque applied to the system corresponding to the usual torques which can be applied between the front cone and the front ferrule during operation of the turbomachine. However, beyond a threshold value of applied torque, the adhesive is no longer able to oppose unscrewing, which is then possible and leads to fracturing of the dried adhesive. The fractured glue is then removed from the respective threads so that it can again induce new glue to repeat the operation.
    The rotation stop system may also include the combination of a polymer 50 ring and reversible glue.
    It goes without saying that the scope of the invention is not limited to the stop systems described above. A person skilled in the art understands that it is also possible to allow the rotation to be stopped by means of mechanical rotation-arresting elements known to those skilled in the art, such as for example the association of orifices practiced in the tangential surfaces of the respective flanges, and of stop screw, these mechanical elements can be used to replace the means described above or in combination with these.
    ίο
    Screwing and unscrewing
    The front cone and front ferrule are screwed and unscrewed using specialized tools.
    To this end, are supported at a radially outer surface 6 of the front cone, support points 60 of clamping tools, at least three in number, and distributed evenly over the entire surface of the
    With reference to FIGS. 3, 4a, 4b, 5a and 5b, these support points are advantageously formed in hollow relative to the radially external surface 6 of the cone, to allow the engagement of a tightening tool. For example, the support points 60 can be formed by notches formed in a radially external surface of the front cone, for example circular notches. Alternatively, these support points can also take the form of flats or grooves. By groove is understood a support point in the form of a hollow which has a preferred transverse dimension. In any case, these support points can take any shape depending on the type of clamping tool used during screwing.
    The proposed assembly therefore allows a simplified and sealed assembly of a front cone on a front shell of a turbomachine.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Set (1) comprising:
    a front cone (3) of a turbomachine, a front ferrule (5) of a turbomachine, downstream of the cone relative to an air flow in the turbomachine, a seal (40) disposed between the front cone and the ferrule front, the assembly being characterized in that the front cone and the front ferrule each comprise a circumferential thread (33, 38), said threads (33, 38) being adapted to cooperate so as to allow mounting by screwing of the front cone (3) on the front ferrule (5), the assembly ensuring compression of the seal (40) between said front cone (3) and said front ferrule (5).
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the cone (3) and the ferrule (5) before each comprise an assembly surface (32, 37) carrying a respective thread (33, 38), said surface (32, 37 ) being a tangential annular surface centered on an axis (XX) of the turbomachine.
    [3" id="c-fr-0003]
    3. The assembly of claim 2, wherein the assembly surface (32) of the front cone (3) is radially internal to said cone (3), and wherein the assembly surface (37) of the front ferrule is radially external to said shell.
    [4" id="c-fr-0004]
    4. The assembly of claim 2, wherein the assembly surface (32) of the front cone (3) is radially external to said cone (3), and wherein the assembly surface (37) of the front ferrule (5 ) is radially internal to said ferrule (5).
    [5" id="c-fr-0005]
    5. Assembly according to one of the preceding claims, in which each assembly surface (32, 37) of the cone (3) and of the ferrule (5) comprises a guide surface (34, 39) adjacent to the respective circumferential thread (33, 38).
    [6" id="c-fr-0006]
    6. The assembly of claim 5, wherein the guide surface (34, 39) is disposed upstream of the thread (33, 38) relative to the direction of flow of air in the turbomachine.
    [7" id="c-fr-0007]
    7. Assembly according to one of the preceding claims, in which the cone (3) and the ferrule (5) before comprise a radial annular surface (32, 36) relative to the axis (XX), said surfaces (32, 36) being adapted to come into contact with one another during screwing, so as to compress the annular seal (40) disposed between said surfaces.
    [8" id="c-fr-0008]
    8. Assembly according to one of the preceding claims, further comprising a system for stopping the threads in relative rotation.
    [9" id="c-fr-0009]
    9. The assembly of claim 8, wherein the rotation stop system comprises a polymer ring (50) mounted on an upstream end of a thread (33, 38) and / or a reversible adhesive.
    [10" id="c-fr-0010]
    10. Assembly according to one of the preceding claims, in which the front cone (3) comprises a radially external surface (6) comprising at least three support points (60) of a clamping tool, said points being regularly distributed on the circumference of said surface.
    [11" id="c-fr-0011]
    11. The assembly of claim 10, wherein each fulcrum (60) is formed in hollow relative to the surface, being formed by one of the following group: notch, groove, or flat, of any shape , made at the radially outer surface of the base of the front cone.
    [12" id="c-fr-0012]
    12. Turbomachine, comprising an assembly (1) according to one of the preceding claims.
    1/8
    X
    2/8
    X -
    3/8
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    同族专利:
    公开号 | 公开日
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3990814A|1975-06-25|1976-11-09|United Technologies Corporation|Spinner|
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    WO2010059071A1|2008-11-19|2010-05-27|Kormilchenko Gennady Mstislavi|Controllable pitch propeller hub with automatic blade feathering mechanism|US20180171932A1|2015-06-11|2018-06-21|Safran Aircraft Engines|Assembly comprising an exhaust case and a downstream rotationally symmetrical part|
    US20190211839A1|2018-01-09|2019-07-11|United Technologies Corporation|Assembly for releasable locking of a spinner or nosecone to an engine structure|
    FR3108149A1|2020-03-11|2021-09-17|Safran Aircraft Engines|BLOWER MODULE FOR AN AIRCRAFT TURBOMACHINE|
    法律状态:
    2017-04-27| PLFP| Fee payment|Year of fee payment: 2 |
    2018-01-05| PLSC| Search report ready|Effective date: 20180105 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 3 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1656185|2016-06-30|
    FR1656185A|FR3053430B1|2016-06-30|2016-06-30|TURBOMACHINE ASSEMBLY FOR A SEALED ASSEMBLY OF A FRONT CONE ON A FRONT VIROLE|FR1656185A| FR3053430B1|2016-06-30|2016-06-30|TURBOMACHINE ASSEMBLY FOR A SEALED ASSEMBLY OF A FRONT CONE ON A FRONT VIROLE|
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