• 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 relates to an assembly of a reported fan blade platform (30) on an aeronautical turbomachine fan (2) disk (22), the assembly comprising a fan disk having at least one tooth (25), and at least one platform (30) mounted on the tooth of the fan disk, said platform comprising a casing having a vein wall (31), a bottom wall (32) and two radially extending side walls between the bottom wall and the vein wall. The box of the platform comprises an upstream opening (34) at an upstream end of the platform and a downstream opening (36), and the assembly further comprises a locking key (40) housed in the box and through the upstream and downstream openings of the box, said locking key being locked at each of its ends by locking means (21, 22a). The invention also relates to a turbomachine blower comprising such an assembly, as well as a method of mounting such an assembly.
    公开号:FR3038654A1
    申请号:FR1556458
    申请日:2015-07-08
    公开日:2017-01-13
    发明作者:Gaillard Thomas Alain De；Alexandre Bernard Marie Boisson；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 therefore to overcome such disadvantages by proposing an assembly of a reported 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 fan disk tooth, said platform comprising a casing having a vein wall, a bottom wall and two side walls extending radially between the bottom wall and the vein wall.
    According to the invention, the box of the platform comprises an upstream opening at an upstream end of the platform and a downstream opening, and the assembly further comprises a locking key housed in the box and passing through the upstream openings. and downstream of the box, said locking key being locked at each of its ends by locking means.
    This assembly, applicable to any type of reported platform for turbomachine blower as soon as it comprises a box, reduces the hub ratio by providing radial retention of the platform through the locking key. The dimensioning of the locking key makes it possible to modify the hub ratio as needed. More specifically, a reduction in the thickness of the locking key, in particular upstream, reduces the hub ratio.
    In addition, the use of the locking key makes it possible to take advantage of the structure of the box of the platform, because the key makes it possible to distribute on a larger surface the forces on the bottom wall of the box.
    Also, in the case where the box comprises an organic matrix composite material made from a fiber reinforcement densified by a matrix, these forces (mainly in tension) are transferred into the side walls of the box, along the fibers of the reinforcement , which offers even better mechanical strength of the platform.
    Finally, the number of parts needed to mount such an assembly is greatly reduced through the use of the locking key.
    Preferably, the locking element locking the locking key at its downstream end is a hook protruding from the tooth of the fan disk.
    Also preferably, the assembly further comprises an upstream ferrule, locking the locking key at its upstream end being provided by said upstream ferrule.
    In this case, the locking key may have at its upstream end a folded portion extending radially along an upstream face of the tooth of the fan disk, said folded portion being traversed by a fixing element ensuring the mounting of the upstream ferrule on the fan disk. In addition, in certain embodiments of the invention, the folded portion of the locking key is extended by an axial portion positioned under the tooth of the fan disk.
    In other embodiments of the invention, the upstream end of the locking key is locked in a housing made in the upstream shell.
    Advantageously, the bottom wall of the box is pierced with an opening through which a hook protrudes from the tooth of the fan disc, said hook being configured to be traversed by the locking key housed in the box.
    The lock key may comprise an organic matrix composite material made from a matrix densified fiber reinforcement, or, alternatively, may be made from a metal or metal alloy.
    The locking key may be a flat bar or a cylindrical rod. The invention also relates to an aeronautical turbomachine fan comprising an assembly of a platform on a fan disk such as that presented above, in which the fan disk has at least two teeth delimiting between them a groove, and at least one blade equipped with a foot mounted in the groove of the fan disk.
    Finally, the invention also relates to a method of mounting an assembly such as that presented above, the method comprising: approaching a substantially radial direction of the platform on the tooth of the fan disk, the insertion of the locking key in the box of the platform through the upstream opening of the box, and the locking of the locking key at its ends by locking means.
    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 view of a platform intended to be used in an assembly according to the invention, and - Figures 4 to 7 are longitudinal sectional views of reported platform assemblies of fan blades on a fan disk, according to different embodiments 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 in 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 takes the form of a box with a vein wall 31, forming the upper face or external platform 30 and having an inclined profile, a bottom wall 32 which allows the platform to rest on the tooth 25 of the disk 22 when the turbomachine is stopped, and two side walls 33 (only one of the two walls) is visible in FIG. 3) extending radially between the bottom wall 32 and the vein wall 31. The bottom wall 32 of the platform 30 comprises a horizontal part 32a and an inclined part 32b, in order to reduce the overall mass of the platform 30. Alternatively, a platform 30 'box also according to the invention may have a bottom wall 32' (Figure 5) which is flat.
    The platforms 30, 30 'can be made, in a manner known per se, of organic matrix composite material comprising a fiber reinforcement densified by a matrix.
    The platform 30 has at its upstream end an upstream opening 34 which may for example be pierced in the box. In addition, the platform 30 also has at the junction between the horizontal portion 32a and the inclined portion 32b of the bottom wall 32 a downstream opening 36. The downstream opening 36 can be pierced directly into the bottom wall 32. Alternatively , the downstream opening 36 'of the platform 30' (Figure 5) may be formed by the perforated portion 36 'already present downstream of the box of the platform 30' without requiring additional drilling.
    An assembly using 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.
    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 by means of fasteners 23b. The shell 21 is fixed on the fan disk 22 by means of fasteners 21a.
    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.
    According to the invention, the assembly also comprises a locking key 40 here taking the form of a flat bar 40 housed in the box of the platform 30 and passing through the upstream opening 34 and the downstream opening 36 of the box, slightly protruding from each side of the box. This bar 40 ensures a homogeneous retention of the platform 30 along the horizontal portion of the bottom wall 32a along the tooth 25 of the disc 22.
    The bar 40 may be made of organic matrix composite material, comprising a fiber reinforcement densified by a matrix. Alternatively, the bar 40 may comprise a metal or a metal alloy.
    The bar 40 is blocked at its downstream end by a locking element here taking the form of a hook 22a protruding downstream of the disk tooth. Upstream, the bar 40 is blocked by the upstream shell 21 which may further comprise a housing 21b for receiving the upstream end of the bar 40.
    In the case where the bottom wall of the box of the platform 30 'is a simple horizontal wall 32' (FIG. 5), the bar 40 passes through the box through the upstream opening 34 and through the downstream opening 36 'already present in the box, without requiring drilling of the bottom wall as in the example of Figure 4.
    In the assembly example shown in FIG. 5, the bottom wall of the box 32 'is pierced with an opening 32a' through which a hook 22b protrudes from the tooth 25 of the disk 22. The hook 22b is configured to be crossed by the bar 40 and block radially. In this way, additional retention of the bar 40 on the tooth of the disc is obtained thanks to the hook 22b. The hook 22b still provides better retention of the platform 30 'and limits the bending of the bar 40 due to centrifugal forces when the turbomachine is in operation. Thus, the presence of this intermediate hook 22b makes it possible to reduce the thickness of the bar 40. The assembly example of FIG. 6 differs from the examples presented above in that the bar 40 'acting as a locking key presents its upstream end a folded portion 40a 'extending radially along an upstream face 25a of the tooth 25 of the disk 22. The folded portion 40a' is pierced so as to be traversed by the fastener 21a of the ferrule upstream 21 on the disk 22 of the fan.
    In FIG. 7, the bar 40 "also has a folded portion 40a" similar to the portion 40a 'of the bar 40' of FIG. 6, which is extended by an axial portion 40b "positioned under the tooth 25 of the disc 22. This configuration further improves the radial retention of the bar 40 "and the platform 30 on the disc.
    Finally, to mount an assembly according to the invention, the platform 30, 30 'is first approached in a substantially radial direction towards the tooth of the disc until the bottom wall 32', or at least its part horizontal 32a, or in contact with the tooth 25 of the disc 22 (it will also be ensured that the flange 23a of the downstream drum 23 comes to be placed on the assembly step 31a of the platform 30, 30 '); then the locking key 40, 40 ', 40 "is inserted into the upstream opening 34 until it also passes through the downstream opening 36, 36' and abuts against the hook 22a present on the tooth 25 ( or a blocking element present on the downstream drum 23), and finally locking the locking key 40, 40 ', 40 "upstream by coming to fix the upstream ferrule 21 on the tooth 25.
    Note that the shape of the locking key 40, 40 ', 40 "is not limited to a flat bar as in the previous examples, but can take various forms, for example a cylindrical rod, or a rod taking the The shape of a half-cylinder A plane bar makes it possible in particular to reduce the hub ratio, while a cylindrical rod makes it possible to better distribute the forces at the bottom of the box and to ensure a more homogeneous transition of the forces. the shape of a half-cylinder is a compromise between these two forms of locking keys.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Assembly of a platform (30, 300 reported fan blade on a disc (22) of aeronautical turbomachine fan (2) (1), the assembly comprising a fan disk having at least one tooth (25). ), and at least one platform (30, 300 mounted on the tooth of the fan disc, said platform comprising a casing having a vein wall (31), a bottom wall (32, 320 and two side walls (33) s extending radially between the bottom wall and the vein wall, characterized in that the box of the platform comprises an upstream opening (34) at an upstream end of the platform and a downstream opening (36, 360, and in that it further comprises a locking key (40, 40 ', 40'0 housed in the box and passing through the upstream and downstream openings of the box, said locking key being locked at each of its ends by means of blocking (21, 22a).
    [2" id="c-fr-0002]
    2. An assembly according to claim 1, characterized in that the locking element ensuring the locking of the locking key at its downstream end is a hook (22a) projecting from the tooth of the fan disk.
    [3" id="c-fr-0003]
    3. Assembly according to any one of claims 1 to 2, characterized in that it further comprises an upstream ferrule (21), locking the locking key (40, 40 ', 40 ") at its upstream end being provided by said upstream ferrule.
    [4" id="c-fr-0004]
    4. An assembly according to claim 3, characterized in that the locking key has at its upstream end a folded portion (40a ', 40a ") extending radially along an upstream face (25a) of the tooth (25). ) of the fan disk (22), said folded portion being traversed by a fastening element (21a) for mounting the upstream shell (21) on the fan disk.
    [5" id="c-fr-0005]
    5. An assembly according to claim 4, characterized in that the folded portion (40a ") of the locking key is extended by an axial portion (40b") positioned under the tooth (25) of the disk (22) blower.
    [6" id="c-fr-0006]
    6. An assembly according to claim 3, characterized in that the upstream end of the locking key is locked in a housing (21b) formed in the upstream shell (21).
    [7" id="c-fr-0007]
    7. Assembly according to any one of claims 1 to 6, characterized in that the bottom wall (320 of the box is pierced with an opening (32a ') traversed by a hook (22b) projecting from the tooth (25). ) of the fan disk (22), said hook being configured to be traversed by the locking key (40) housed in the box.
    [8" id="c-fr-0008]
    8. Assembly according to any one of claims 1 to 7, characterized in that the locking key (40, 40 ', 40 ") is a flat bar or a cylindrical rod.
    [9" id="c-fr-0009]
    Aeronautical turbomachine blower comprising an assembly of a platform (30, 300 on a disk (22) of a fan (2) according to any one of claims 1 to 8, wherein the fan disk 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.
    [10" id="c-fr-0010]
    10. A method of mounting an assembly according to any one of claims 1 to 8, the method comprising: approach in a substantially radial direction of the platform (30, 30 ') on the tooth (25) of the disk ( 22), the insertion of the locking key (40,40 ', 40 ") into the box of the platform through the upstream opening (34) of the box, and the locking of the locking key at its ends. by the locking means (21, 22a).
    类似技术:
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    同族专利:
    公开号 | 公开日
    GB201611933D0|2016-08-24|
    US20170097009A1|2017-04-06|
    GB2541114B|2020-04-15|
    FR3038654B1|2017-08-04|
    US10233939B2|2019-03-19|
    GB2541114A|2017-02-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6634863B1|2000-11-27|2003-10-21|General Electric Company|Circular arc multi-bore fan disk assembly|
    US20080226458A1|2007-03-16|2008-09-18|Snecma|Turbomachine fan|
    FR2988426A1|2012-03-20|2013-09-27|Snecma|Inter blade platform for fan of e.g. turbo jet engine, of aircraft, has upstream end portion and/or downstream end portion provided with upstream and downstream wings prolonging wall, and assembly flanges extended axially beyond wings|
    EP2837774A1|2013-08-14|2015-02-18|Rolls-Royce plc|Annulus filler and corresponding stage and gas turbine engine|
    WO2015076900A2|2013-10-11|2015-05-28|United Technologies Corporation|Fan rotor with integrated platform attachment|FR3082876A1|2018-06-21|2019-12-27|Safran Aircraft Engines|BLOWER COMPRISING A PLATFORM AND A LOCKING LATCH|
    FR3082871A1|2018-06-21|2019-12-27|Safran Aircraft Engines|BLOWER COMPRISING A PLATFORM AND A LOCKING LATCH|US5281096A|1992-09-10|1994-01-25|General Electric Company|Fan assembly having lightweight platforms|
    US6447250B1|2000-11-27|2002-09-10|General Electric Company|Non-integral fan platform|
    GB201104994D0|2011-03-25|2011-05-11|Rolls Royce Plc|a rotor having an annulus filler|
    US9759226B2|2013-02-15|2017-09-12|United Technologies Corporation|Low profile fan platform attachment|
    WO2015088680A1|2013-12-13|2015-06-18|United Technologies Corporation|Fan blade platform spacer mounting|
    FR3029563B1|2014-12-08|2020-01-17|Safran Aircraft Engines|LOW HUB RATIO PLATFORM|
    FR3033180B1|2015-02-26|2018-07-13|Safran Aircraft Engines|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|US11092021B2|2019-05-06|2021-08-17|Raytheon Technologies Corporation|Fan platform with core and skin|
    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
    FR1556458A|FR3038654B1|2015-07-08|2015-07-08|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|FR1556458A| FR3038654B1|2015-07-08|2015-07-08|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|
    US15/205,265| US10233939B2|2015-07-08|2016-07-08|Aviation turbine engine fan assembly including a fitted platform|
    GB1611933.1A| GB2541114B|2015-07-08|2016-07-08|An aviation turbine engine fan assembly including a fitted platform|
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