• 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:
    An assembly of an attached fan blade platform (30) (26) on an aeronautical turbomachine fan disk (22), the assembly comprising a fan disk (22) having at least one tooth (25) and at least one at least one platform (30) mounted on the tooth (25) of the fan disk. The tooth of the fan disk comprises a lug (25a) extending in the axial extension of said tooth upstream, and the platform comprises at its upstream end a locking ring (34) in which is intended to be housed the paw of the tooth of the fan disk. The invention also relates to a turbomachine blower (2) comprising such an assembly, as well as a method of mounting such an assembly.
    公开号:FR3038653A1
    申请号:FR1556459
    申请日:2015-07-08
    公开日:2017-01-13
    发明作者:Gaillard Thomas Alain De；Alexandre Bernard Marie Boisson；Matthieu Arnaud Gimat；Audrey Laguerre
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to the general field of aeronautical turbomachines, and more specifically to the field of the reported blades of the blades of the blower of an aerospace turbomachine.
    In a turbomachine, the reported blades of blades of the fan must provide several functions. From an aerodynamic point of view, these platforms have the primary function of defining the flow vein of the air. In addition, they must also be able to withstand significant effort without deforming and remaining integral with the disc that carries them.
    In order to satisfy these different requirements, certain configurations have been proposed in which the platforms have a first part making it possible to define the air flow vein and to ensure the retention of the platform when the engine is rotating, and a second part to limit the deformations of the first part under the effects of centrifugal forces and maintain the platform in position when the engine is stopped.
    In existing solutions, the platform can take the form of a box with a two-dimensional vein wall retained downstream by a drum and upstream by a ferrule, the upstream retention by the ferrule being carried out above the tooth of the fan disk (a flange of the ferrule blocking the axle axially and radially upstream).
    Such upstream retention performed above the disk tooth with a ferrule has the disadvantage of imposing a high hub ratio, the hub ratio being the ratio of the radius taken between the axis of rotation and the point of the edge. attacking the dawn flush on the surface of the platform, on the radius between the axis of rotation and the point of the outermost leading edge.
    In order to optimize the performance of the blower, and more generally of the turbomachine, it is desirable to have an assembly of an attached blower blade platform on a blower disc which has the lowest hub ratio. possible.
    Object and summary of the invention
    The main purpose of the present invention is thus to overcome such drawbacks by proposing an assembly of an attached fan blade platform on an aeronautical turbomachine fan disk, the assembly comprising a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, characterized in that the tooth of the fan disk comprises a tab extending in the axial extension of said tooth upstream, and in that the platform comprises at the level of its upstream end a locking ring in which is intended to be housed the lug of the tooth of the fan disk.
    This assembly, applicable to any type of aeronautic turbomachine fan blade reporting platform, makes it possible to reduce the hub ratio by ensuring radial retention of the platform by means of the upstream locking ring.
    In addition, an assembly according to the invention is advantageous in that it does not require additional patches to ensure the radial retention of the platform upstream, since it is provided by the locking ring integrated into the platform . Also, a tooth of the fan disk usually already has a tab that extends upstream, which reduces the operations required to design an assembly according to the invention and avoids having to redefine the shape of the surrounding parts. The assembly is also advantageous in that it allows to leave a tangential degree of freedom at the platform, by varying the size of the locking ring, with respect to the section of the tab. This degree of freedom makes it possible to avoid the damage caused in particular by the ingestion of objects in the blower.
    Advantageously, the platform can be made of organic matrix composite material made from a fiber reinforcement densified by a matrix.
    Preferably, the assembly further comprises a downstream collar attached to the fan disk and blocking the platform downstream.
    Also preferably, the assembly further comprises an upstream ferrule fixed on the fan disk and axially blocking the platform upstream.
    In an exemplary embodiment, the tab of the disc tooth and the locking ring have substantially identical sections.
    In another embodiment, the assembly further comprises a wedge positioned inside the locking ring so as to lock the platform on the flap of the tooth of the fan disk.
    The tooth of the disc may have a flat portion extending over a first length, the tab of the disc tooth extending over a second length representing between 4% and 15% of said first length.
    In exemplary embodiments, the platform comprises a casing having a vein wall, a bottom wall and two lateral walls extending radially between the bottom wall and the vein wall. With this arrangement, and when such a platform is made of composite material from a fiber reinforcement densified by a matrix, the upstream portion of the box works in traction in the direction of the fibers thanks to the locking ring, which ensures good mechanical strength of the whole. The invention also relates to an aerospace turbine engine fan comprising an assembly such as that described above, in which the fan disk has at least two teeth delimiting between them a groove, and at least one blade provided with a foot mounted in the groove. of the fan disk. The invention also relates to a method of mounting an assembly such as that described above, the method comprising: approaching in a radial direction of the platform on the tooth of the fan disk by positioning the locking ring in front of the paw of the tooth of the fan disk, and the axial translation from upstream to downstream of the platform along the tooth of the fan disk.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate embodiments having no limiting character. In the figures: FIG. 1 is a diagrammatic sectional view of a turbomachine according to the invention, FIG. 2 is a diagrammatic view along the direction II of the fan of FIG. 1, FIG. schematic perspective of a platform intended to be used in an assembly according to the invention, - Figures 4 and 5 are respectively a schematic sectional view and a view from upstream of an assembly according to an embodiment of the invention. invention, and - Figure 6 is a view from the upstream of an assembly according to another embodiment of the invention.
    Detailed description of the invention
    In this presentation, the terms "longitudinal", "transverse", "lower", "superior" and their derivatives are defined in relation to the principal direction of the platform in question; the terms "transverse", "radial", "tangential", "interior", "exterior" and their derivatives are themselves defined with respect to the main axis of the turbomachine; finally, the terms "upstream" and "downstream" are defined with respect to the flow direction of the fluid passing through the turbomachine. Also, unless otherwise indicated, the same reference characters in different figures denote the same characteristics.
    Figure 1 shows a schematic longitudinal sectional view of a turbofan engine 1 centered on the axis A-A according to the invention. It comprises, from upstream to downstream: a fan 2, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, and a low-pressure turbine 7.
    Figure 2 shows a schematic view of the fan 2 of Figure 1 along the direction II. The blower 2, object of the present invention, comprises a fan disk 22 in which a plurality of grooves 24 are formed at its outer periphery. These grooves 24 are rectilinear and extend axially from upstream to downstream all along the disc 22. They are also regularly distributed around the axis AA of the disc 22. In this way, each groove 24 defines with its neighbor a tooth 25 which also extends axially from upstream to downstream along the disc 22. Equally, a groove 24 is defined between two adjacent teeth 25.
    The fan 2 further comprises a plurality of blades 26 of curvilinear profile (only four blades 26 have been shown in Figure 2). Each blade 26 has a foot 26a which is mounted in a respective groove 24 of the fan disk 22. For this purpose, the root 26a of a blade 26 may have a fir or dovetail shape adapted to the geometry of the blades. grooves 24.
    Finally, the fan 2 comprises a plurality of reported platforms 30, each platform 30 being mounted in the gap between two adjacent fan blades 26, in the vicinity of the feet 26a thereof, in order to delimit, on the inside, a vein annular air inlet into the blower 2, the vein being delimited on the outer side by a fan casing.
    Figures 1 and 2 also show an inner radius RI and an outer radius RE. The inner radius RI corresponds to the radius between the axis of rotation AA and the point of the leading edge of a blade 26 flush with the surface of a platform 30. The outer radius RE corresponds to the radius taken between the axis of rotation AA and the point of the leading edge of an outermost blade 26. These two radii RI, RE are those used in the calculation of the hub ratio RI / RE that the assembly according to the invention proposes to decrease (in particular reducing the internal radius RI). In other words, the reduction of the hub ratio, in particular by acting on the internal radius RI, amounts to bringing the aerodynamic stream of air intake closer to the fan disk.
    A platform 30 intended to be used in an assembly according to one embodiment of the invention is shown in perspective in FIG. 3. The platform 30 here takes the form of a box with a vein wall 31, forming the upper face. or outside of the platform 30 and having an inclined profile, a bottom wall 32 which allows the platform to rest on the tooth 25 of the disc 22 when the turbomachine is stopped, and two side walls 33 extending radially between the bottom wall 32 and the vein wall 31.
    Such a platform 30 can be made, in a manner known per se, of organic matrix composite material comprising a matrix-densified fiber reinforcement.
    According to the invention, the platform 30 comprises at its upstream end a locking ring in which is intended to be housed the tab 25a (Figures 4, 5 and 6) of a tooth 25 of the disk 22. In this example embodiment, the ring 34 has a trapezoidal section.
    An assembly implementing the platform 30 presented previously with reference to FIG. 3 will now be described with reference to FIG. 4. This figure illustrates in more detail a blower 2 according to one embodiment of the invention (sectional view at a tooth of the fan disk, according to the sectional plane IV visible in Figure 5).
    FIG. 4 shows in particular a blower 2 comprising: an upstream shell 21, the fan disk 22 and a downstream drum 23 (also called a "booster" drum) provided with a retaining flange 23 to cooperate with an assembly step 31a of the platform 30 downstream. The downstream drum 23 is fixed on the fan disk 22 at a bore 25b made in a step downstream of the tooth 25, by means of fasteners 23b. The shell 21 is fixed on the fan disk 22 at the tab 25a which axially extends the tooth 25 of the disc 22 upstream, through fasteners 21a.
    Note that the tooth 25 of the disc 22 has a flat portion (between the downstream step comprising the bore 25b, and the upstream end of the tab 25a) which extends on a first length L1, and that the leg 25a of the disk tooth extends over a second length L2 which can represent between 4% and 15% of the first length L1. The locking ring 34 extends axially over a length preferably less than the length L2 of the tab 25a.
    The fan disk 22 is coupled with the drive shaft of the low-pressure turbine 7 of the turbomachine, so that in operation, the upstream shell 21, the fan disk 22, the blades 26, and the downstream drum 23 are integrally rotated by the low-pressure turbine 7. The platforms 30, mounted between the upstream ferrule 21 and the downstream drum 23, and axially locked by these two elements, are thus also driven integrally in rotation.
    The platform 30 is retained radially upstream by the locking ring 34 which is "threaded" on the tab 25a. In other words, the tab 25a of the tooth 25 is inserted into the locking ring 34 of the platform 30.
    Advantageously, the tab 25a has a trapezoidal section intended to cooperate with the ring 34 which also has a trapezoidal internal section, substantially identical to that of the ring. In this way, the platform 30, once threaded on the tab 25a, is blocked in the radial and tangential directions. Of course, any other type of section is possible for the tab 25a or the ring 34, for example circular, rectangular, etc.
    FIG. 5 shows a view from upstream (in the direction V) of FIG. 4) of an assembly according to the invention comprising a fan disc 22 on which is mounted a platform 30, such as that of FIG. .
    FIG. 6 illustrates another example of assembly according to the invention also comprising a disc 22 on which a platform 30 'is mounted. Unlike the assembly shown in Figures 4 and 5, the locking ring 34 'of the platform 30' of the assembly of Figure 6 has a rectangular section larger than the trapezoidal section of the tab 25a of the tooth 25 of the disc 22. A wedge 40 is then positioned between the ring 34 'and the tab 40 (when the tab 40 is inserted into the ring), in order to fill the space between these two elements and to block radially and tangentially the platform upstream. The shim 40 has a section that corresponds substantially to the shape of the space left between the ring 34 'and the tab 25a, here in the form of "U". The use of this wedge 40 is advantageous because it allows to be able to mount the platform 30 'with a certain tangential clearance, then to lock with the wedge. Indeed, during the assembly of the fan, the complex and bulky profile of the blades and platforms leaves a very small margin of maneuver to mount the platforms on the disk. Thus, the mounting of the blower is facilitated with the possibility of rotating tangentially (direction of the arrows 10 in Figure 6) the platforms.
    Finally, to mount a blower according to the invention, it is first possible to mount the downstream drum 23 on the disk 22, then a part of the fastening element 21a (for example a nut) which is intended to be put in place. to ensure the fixing of the upstream ferrule 21 on the disk 22. The platform 30, 30 'of the tooth of the disk is then approached in a radial direction so that the locking ring 34, 34' is opposite the leg 25a and aligned therewith. Then we translate the platform 30, 30 'axially from upstream to downstream by making it follow the tooth of the disc, until it is blocked downstream by the downstream drum 23. Finally, the upstream ferrule 21 is mounted on the disk 22 and fixed by the fastening elements 21a.
    Note that, in the case where a shim 40 is used, it is possible to rotate the platform 30 'tangentially at the moment when it is threaded onto the tab 25a of the disk tooth, then block it with the shim 40 before coming up the upstream ferrule 21.
    Note also that the invention does not apply only to the box platforms as in the examples described above, but can be applied to any type of reported fan blade platform.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Assembly of an attached platform (30, 300 of fan blade on a disc (22) of aeronautical turbomachine fan (2) (1), the assembly comprising a fan disc having at least one tooth (25). ) and at least one platform (30, 300 mounted on the tooth of the fan disk, characterized in that the tooth of the fan disk comprises a lug (25a) extending in the axial extension of said tooth upstream, and in that the platform comprises at its upstream end a locking ring (34, 340 in which is intended to be housed the tooth lug of the fan disk.
    [2" id="c-fr-0002]
    2. Assembly according to claim 1, characterized in that it further comprises a downstream shell (23) fixed on the fan disk and blocking the platform downstream.
    [3" id="c-fr-0003]
    3. Assembly according to any one of claims 1 and 2, characterized in that it further comprises an upstream ferrule (21) fixed on the fan disk and axially blocking the platform upstream.
    [4" id="c-fr-0004]
    4. Assembly according to any one of claims 1 to 3, characterized in that the tab (25a) of the disc tooth and the locking ring (34) have substantially identical sections.
    [5" id="c-fr-0005]
    5. Assembly according to any one of claims 1 to 4, characterized in that it further comprises a shim (40) positioned inside the locking ring (340 so as to block the platform (300 on the tab (25a) of the tooth of the fan disk.
    [6" id="c-fr-0006]
    6. Assembly according to any one of claims 1 to 5, characterized in that the tooth (25) of the disc (22) has a flat portion extending on a first length (Li), the flap of the disc tooth extending over a second length (L2) representing between 4% and 15% of said first length.
    [7" id="c-fr-0007]
    7. Assembly according to any one of claims 1 to 6, characterized in that the platform (30, 300 comprises a box having a vein wall (31), a bottom wall (32) and two side walls (33). extending radially between the bottom wall and the vein wall.
    [8" id="c-fr-0008]
    Aeronautical turbomachine blower (2) comprising an assembly of a platform (30, 300 on a blower disc (22) according to any of claims 1 to 7, wherein the blower disc (22) ) has at least two teeth (25) delimiting between them a groove (24), and at least one blade (26) provided with a foot (26a) mounted in the groove of the fan disk.
    [9" id="c-fr-0009]
    9. A method of mounting an assembly according to any one of claims 1 to 7, the method comprising: the approach in a radial direction of the platform (30, 300 on the tooth (25) of the disc (22) of blower by positioning the locking ring (34, 340 in front of the tab (25a) of the tooth of the fan disk, and the axial translation from upstream to downstream of the platform along the tooth of the fan disk .
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    同族专利:
    公开号 | 公开日
    EP3320181A1|2018-05-16|
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    RU2018104653A|2019-08-08|
    RU2704572C2|2019-10-29|
    CN107949685B|2020-07-17|
    US20180202458A1|2018-07-19|
    WO2017006054A1|2017-01-12|
    JP2018525558A|2018-09-06|
    CN107949685A|2018-04-20|
    US10612558B2|2020-04-07|
    RU2018104653A3|2019-08-08|
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    法律状态:
    2016-07-20| PLFP| Fee payment|Year of fee payment: 2 |
    2017-01-13| PLSC| Search report ready|Effective date: 20170113 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 6 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1556459A|FR3038653B1|2015-07-08|2015-07-08|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|FR1556459A| FR3038653B1|2015-07-08|2015-07-08|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|
    PCT/FR2016/051711| WO2017006054A1|2015-07-08|2016-07-06|Rotary assembly of an aeronautical turbomachine comprising an added-on fan blade platform|
    CA2991431A| CA2991431A1|2015-07-08|2016-07-06|Rotary assembly of an aeronautical turbomachine comprising an added-on fan blade platform|
    JP2018500552A| JP6736654B2|2015-07-08|2016-07-06|Rotating Assembly of Aero Turbo Machine with Retrofit Fan Blade Platform|
    CN201680050308.4A| CN107949685B|2015-07-08|2016-07-06|Rotating assembly of an aircraft turbine comprising an additional blower blade platform|
    US15/741,839| US10612558B2|2015-07-08|2016-07-06|Rotary assembly of an aeronautical turbomachine comprising an added-on fan blade platform|
    EP16745791.0A| EP3320181B1|2015-07-08|2016-07-06|Rotor assembly of an aeronotical turbine engine comprising an inter-blade platform of a fan|
    RU2018104653A| RU2704572C2|2015-07-08|2016-07-06|Rotating assembly of aircraft gas turbine engine, aircraft gas turbine engine fan comprising such unit, and method of mounting said assembly|
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