• 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 fan blade platform on an aeronautical turbomachine fan disk, the assembly comprising: a fan disk (22) comprising at least one tooth (25) from which an element locking device (34) protrudes radially outwards; and at least one platform (30) comprising a well having a vein wall (31), a bottom wall (32) and two side walls (35) extending radially between the bottom wall and the vein wall, the bottom wall of the platform comprising at least one opening (33) adapted to receive a blocking element (34) of the tooth of the fan disk so as to maintain the platform radially on the fan disk. The invention also relates to a blower (2) comprising in particular such an assembly.
    公开号:FR3033180A1
    申请号:FR1551640
    申请日:2015-02-26
    公开日:2016-09-02
    发明作者:Gaillard Thomas Alain De；Caroline Jacqueline Denise Berdou；Alexandre Bernard Marie Boisson；Matthieu Arnaud Gimat
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the general field of aeronautical turbomachines, and more specifically to the field of the reported platforms of 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 15 have a first part making it possible to define the flow vein of the air 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.
    [0002] In existing solutions, the platform may take the form of a box with a two-dimensional vein wall retained downstream by a drum and upstream by a shell, the upstream retention by the shell being carried out above the tooth of the fan disk (a flange of the ferrule blocking axially and radially platform 25 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 with 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 disk which has the highest hub ratio. low possible.
    [0003] SUMMARY OF THE INVENTION The main object of the present invention is therefore to reduce the hub ratio by proposing an assembly of an attached fan blade platform on an aeronautical turbomachine fan disk, the assembly comprising: a fan disk comprising at least one tooth from which a locking member projects radially outwardly; and at least one 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 bottom wall of the platform comprises at least one opening adapted to receive a locking element 15 of the tooth of the fan disk so as to radially maintain the platform on the fan disk. The assembly according to the invention is advantageous in that it uses a box platform, whose mechanical strength and resistance to centrifugal forces are known, which is retained radially directly on the tooth of the fan disk by the biasing of at least one locking element present on the tooth. In other words, the radial retention of the platform is no longer carried out by means of ferrules as is the case traditionally, but by the tooth of the disc. Thus, the radius between the axis of rotation of the turbine engine and the point of the leading edge of the blade flush with the surface of the platform can be considerably reduced thanks to the absence of radial retention by a ferrule, which further reduces the hub ratio and in particular improves the performance of the blower. Such an assembly also makes it possible to reduce the number of parts required for the radial retention of the platform since only a blocking element of the tooth and an opening in the bottom wall of the box are necessary. In other words, no additional insert is needed to mount the platform on the disk.
    [0004] 3 0 3 3 1 80 3 Also, the assembly according to the invention, by the reduced number of parts necessary for its assembly, and the box structure of the platform with its opening, allows a saving in weight. In addition, such a configuration makes it possible in particular to preserve a tangential degree of freedom of the platform on the disk, which allows a better holding of the assembly in the event of ingestion of objects in the turbomachine. According to one embodiment of the invention, the blocking element of the fan disk is a hook that can have an L-shaped longitudinal section. Preferably, the bottom wall of the platform comprises a plurality of openings and the The fan disk tooth comprises a plurality of locking elements adapted to be received in the openings of the bottom wall of the platform. Thus, it is possible to increase the number of links between the disk and the platform, which allows to distribute the forces more evenly in the box of the platform, including tensile forces when the disk is rotating. Also preferably, the assembly further comprises an upstream ferrule fixed on the fan disk upstream and a downstream drum attached to the fan disk downstream, the upstream ferrule and the downstream drum axially blocking the platform on the tooth of the fan disk. More preferably, the box is made in one piece of composite material comprising a fiber reinforcement densified by a matrix. The use of such a box allows to further increase the mechanical strength of the platform. Indeed, the assembly of the platform described above imposes a work in traction of the platform when the disc is rotating (under the effect of the centrifugal force in particular), and the fibers of the fibrous reinforcement in the composite material ensure better resistance to this traction by distributing efforts throughout the box. The invention also relates to an aeronautical turbomachine fan comprising an assembly of a fan blade platform on a fan disk 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 disk.
    [0005] Other features and advantages of the present invention will be apparent from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures: FIG. 1 is a schematic 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. longitudinal sectional view along plane III of FIG. 2 of an assembly of a platform on a fan disk according to the invention, and FIG. 4 is a view along direction IV of the platform 15 of FIG. DETAILED DESCRIPTION OF THE INVENTION In this disclosure, the terms "longitudinal", "transversal", "inferior", "superior" and their derivatives are defined relative to the principal direction of the platform under consideration; 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. 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 30, a high-pressure turbine 6, and a low-pressure turbine 7. FIG. 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 is formed at its outer periphery. These grooves 24 are rectilinear and extend axially from upstream to downstream along the entire 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.
    [0006] The blower 2 further comprises a plurality of vanes 26 of curvilinear profile (only four vanes 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-shaped or dovetail shape adapted to the geometry 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 side internal, an annular air inlet vein 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 R1 corresponds to the radius taken 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 ratio of hub 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, by acting on the internal radius RI, amounts to bringing the aerodynamic stream of air inlet in the fan closer to the fan disk. The blower 2 is shown in more detail in FIG. 3 showing a sectional view along a plane III of FIG. 2 at the level of a tooth 25 of the blower disk 22. In this figure, an upstream ferrule 21 can be seen. the fan disk 22, and a downstream drum 23 (also called "booster drum"). The downstream drum 23 has at its upstream end a retaining flange 23a.
    [0007] The upstream shell 21 and the downstream drum 23 are fixed to the fan disk 22 by means of fasteners 21b and 23b, the latter being coupled 3033180 to the drive shaft of the low-pressure turbine 7 of the turbomachine. Thus, 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 shell 21 and the downstream drum 23, and axially locked by these two elements, are thus also driven integrally in rotation. Each platform 30 essentially takes the form of a box with a vein wall 31, forming the upper or outer face of the platform 30, which extends the upstream shell 21 downstream and the downstream drum 23 upstream of in such a way as to delimit with these two elements, on the inside, the air inlet duct in the blower 2. The vein wall 31 thus has an inclined profile, the diameter of the downstream drum 23 being greater than that of the ferrule 21. The vein wall 31 further comprises a downstream assembly step 31a at its downstream end which allows retention downstream of the platform 30 radially and axially through the flange 23a of the downstream drum 23. The platform 30 also includes a bottom wall 32 which allows the platform to rest on the tooth 25 when the motor is at a standstill. This bottom wall 32 does not protrude from the disk tooth 25 upstream and ends substantially at the same level as the latter when the platform 30 is mounted on the tooth 25. Finally, the platform also comprises two side walls 35 (visible in FIG. 4) extending radially between the bottom wall 32 and the vein wall 31. According to the invention, the platform 30 comprises an opening 33 (for example a hole of rectangular shape as illustrated in FIG. 4) in its bottom wall 32, and the tooth 25 of the fan disk 22 comprises a locking element (for example a hook L-shaped longitudinal section 34) projecting radially outwardly of the The opening 33 can be made simply by drilling the box, and the hook 34 can be machined directly in the mass on the tooth 25 of the disc. The hook 34 illustrated in Figure 3 comprises an axial portion 34a and a radial rod 34b.
    [0008] The opening 33 made in the bottom wall of the platform 30 has dimensions compatible with the hook 34 so that the axial portion 34a of the hook can pass through the opening 33 and come over the face. of the bottom wall 32 located inside the box, and that once mounted on the tooth, the platform 30 does not protrude from the tooth 25 upstream. Ideally, the length of the radial rod 34b of the hook 34 is substantially greater than the thickness of the bottom wall 32, and the size of the opening 33 is sufficient for the hook 34 to pass therethrough. In order to ensure that the hook 34 does not alter the integrity of the platform 30 when it is inserted into the opening 33 thereof, the opening 33 may be provided with a reinforcement protecting at least one part of its periphery. Preferably, the reinforcement is present on the parts of the platform 30 likely to be in contact with the hook 34 when the turbomachine is in operation. The reinforcement may for example take the form of a seal or a metal reinforcement fixed around the opening 33 and / or on the bottom wall 32 of the platform 30 in the vicinity of the opening 33. Such a reinforcement allows to spread over a larger area the forces on the platform 30 driven by the hook 34 avoiding the point contacts between these two elements. To assemble the platform 30 on the tooth 25 of the disk on which the downstream drum 23 has been previously mounted, it is first necessary to bring the platform 30 towards the tooth in a substantially radial direction by making sure that the hook 34 is opposite the opening 33. Then, the hook 34 is inserted into the opening 33 and an axial translation is made from the upstream to the downstream of the platform 30 along the tooth 25, so that the hook 34 (thanks to its axial portion 34a) and the tooth 25 grip a part of the bottom wall 32. During this last step, the flange 23a of the downstream drum 23 also holds the platform radially. and block it axially downstream. Finally, the upstream ferrule 21 is fixed on the tooth 25 of the disc 30 to block axially the platform 30 upstream. In this way, the hook 34 and the flange 23a provide radial retention of the platform 30 directly from the tooth 25 of the fan disk 22, the ferrule 21 and the drum 23 for blocking axially. This arrangement does not require the addition of additional fasteners 35 on the platform, so the assembly is shorter, easier, less expensive and allows a saving in weight.
    [0009] It should be noted that the bottom wall 32 of the platform 30 may comprise several openings 33 (for example distributed longitudinally or transversely), and that the tooth 25 may comprise several hooks 34 whose position corresponds to the position 5 of the openings 33. Thus, it is possible to increase the number of connections between the tooth 25 and the platform 30 in order to obtain even better radial retention and to ensure a better distribution of the stresses in the platform 30 and the hooks 34. The box platform according to the invention may be made of a composite material comprising a fiber reinforcement densified by a matrix. Reference can be made to document WO 2013/160584 which describes the fabrication of a platform provided with a box in one piece from a 3D woven fiber reinforcement and densified by a matrix according to a RTM technique (for "Resin Transfer Molding "). Once the box 15 has been made, the opening 33 can be made simply by drilling the bottom wall 32. The invention is not limited only to the openings 33 of rectangular shape and the hooks 34 as blocking elements, other forms of openings and locking elements are of course conceivable.
    权利要求:
    Claims (7)
    [0001]
    REVENDICATIONS1. A blower blade attached platform assembly on an aeronautical turbomachine blower disc, the assembly comprising: a blower disc (22) comprising at least one tooth (25) from which a blocking member ( 34) protrudes radially outwardly; and at least one platform (30) comprising a casing having a vein wall (31), a bottom wall (32) and two side walls (35) extending radially between the bottom wall and the vein wall, characterized in that the bottom wall of the platform comprises at least one opening (33) adapted to receive a blocking member (34) of the tooth of the fan disk so as to radially maintain the platform on the fan disk.
    [0002]
    2. Assembly according to claim 1, characterized in that the blocking element of the fan disk is a hook (34). 20
    [0003]
    3. Assembly according to claim 2, characterized in that the hook (34) has an L-shaped longitudinal section.
    [0004]
    4. An assembly according to any one of claims 1 to 3, characterized in that the bottom wall (32) of the platform comprises a plurality of openings (33), and in that the tooth (25) of the disc blower comprises a plurality of locking elements (34) adapted to be received in the openings of the bottom wall of the platform.
    [0005]
    5. Assembly according to any one of claims 1 to 4, characterized in that it further comprises an upstream shell (21) attached to the fan disk (22) upstream and a downstream drum (23). attached to the fan disk downstream, the upstream collar and the downstream drum axially locking the platform (30) on the tooth (25) of the fan disk. 303 3 1 80 10
    [0006]
    6. Assembly according to any one of claims 1 to 5, characterized in that the box is made in one piece of composite material comprising a fiber reinforcement densified by a matrix.
    [0007]
    An aircraft turbomachine blower (2) comprising: an assembly of a blower blade platform (30) on a blower disc (22) according to any one of claims 1 to 6 wherein the blower disc 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.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3033180B1|2018-07-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20140003958A1|2012-06-29|2014-01-02|United Technologies Corporation|Fairing assembly|
    EP2837774A1|2013-08-14|2015-02-18|Rolls-Royce plc|Annulus filler and corresponding stage and gas turbine engine|GB2541114A|2015-07-08|2017-02-08|Safran Aircraft Engines|An aviation turbine engine fan assembly including a fitted platform|
    EP3312384A1|2016-10-21|2018-04-25|Safran Aircraft Engines|Rotary assembly of a turbine engine provided with a system for axial retention of a blade|
    FR3089258A1|2018-12-03|2020-06-05|Safran Aircraft Engines|Blower comprising an inter-blade platform fixed radially by a sacrificial protective sheet|
    WO2020260810A1|2019-06-26|2020-12-30|Safran Aircraft Engines|Inter-blade platform with a sacrificial box section|
    法律状态:
    2016-02-08| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-02| PLSC| Publication of the preliminary search report|Effective date: 20160902 |
    2017-02-01| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 7 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1551640A|FR3033180B1|2015-02-26|2015-02-26|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|
    FR1551640|2015-02-26|FR1551640A| FR3033180B1|2015-02-26|2015-02-26|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|
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