• 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:
    Turbocomachine bladed wheel with lightweight platforms and low hub ratio. According to the invention, the wheel comprises a disc (22), a plurality of blades, and at least one platform (30) having a vein portion (31), extending from upstream to downstream, and a support portion (32); the support portion (32) has at least one Y-shaped portion comprising a first support arm (34) connected at its end to a first zone (34z) of the vein portion (31), a second support arm (35) connected at its end to a second zone (35z) of the vein portion (31), distinct from the first zone (34z), and a support leg (36) extending radially towards the disk (22) from the junction (33j) between the first and second support arms (34, 35); at least the tooth (25) of the disc (22) facing said platform (30) is provided with at least one notch (41); and the end of the support leg (36) is fixed in a notch (41) of the tooth (25).
    公开号:FR3021693A1
    申请号:FR1454844
    申请日:2014-05-28
    公开日:2015-12-04
    发明作者:Alexandre Bernard Marie Boisson；Caroline Jacqueline Denise Berdou
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present disclosure relates to a bladed wheel, a blower module and a turbomachine comprising light platforms and having a low hub ratio.
    [0002] Such a bladed wheel can in particular be used in the aeronautical field, in aircraft turbojet engines or helicopter turbine engines to name just these examples. STATE OF THE PRIOR ART In an airplane turbojet, the platforms of the various bladed wheels, and in particular of the blower, must perform many functions. Mainly, they must define the air flow vein by minimizing the aerodynamic disturbances at their bladed wheel as well as at the level of other downstream bladed stages: in particular, they must define coherent interfaces to borders with the other floors. They must also be able to withstand significant effort without experiencing significant deformation and without detaching themselves from the disc that carries them to ensure the safety and availability of the engine for commercial use. In order to satisfy these different requirements, certain configurations have been proposed in which the platforms have a first part, which makes 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 to maintain the platform in position when the engine is stopped. In some of these configurations, the platforms assume a box-like shape with a two-dimensional vein portion retained upstream and downstream and carried by a U-shaped support portion. However, such a box-like configuration is bulky, which poses mass and integration problems, leading in particular to a high hub ratio, the hub ratio being the ratio of the radius taken between the axis of rotation and the point of the leading edge of the blade 3021693 2 flush with surface of the platform, on the radius taken between the axis of rotation and the point of the outermost leading edge. In other configurations, the vein portion is both retained upstream and downstream and supported by two arms provided at their distal ends with hooks engaging with hooks carried by the wheel disc. Here again, the complexity of such fixing poses mass and integration problems, also leading to a high hub ratio. There is therefore a real need for a bladed wheel, a blower module and a turbomachine which are lacking, at least in part, the disadvantages inherent in the above-mentioned known configurations. PRESENTATION OF THE INVENTION The present disclosure relates to a bladed wheel for a turbomachine, comprising a disc, able to be coupled to a shaft of the turbomachine, the circumference of which has a succession of grooves and teeth, a plurality of blades mounted in grooves of the disk, and at least one platform, provided between two blades facing a tooth of the disk, having a portion of vein, extending from upstream to downstream, and a support portion; the support portion has at least one Y-shaped portion comprising a first support arm connected at its end to a first zone of the vein portion, a second support arm connected at its end to a second zone of the vein portion, separate of the first zone, and a support leg extending radially towards the disk from the junction between the first and second support arms; at least the disc tooth facing said platform is provided with at least one notch; and the end of the support leg is fixed in a notch of the tooth.
    [0003] In this disclosure, the terms "longitudinal", "transversal", "lower", "superior" and their derivatives are defined relative to the main direction of the blades; the terms "axial", "radial", "tangential", "interior", "outside" 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 of air in the turbomachine.
    [0004] 3021693 3 With such a configuration, it is possible to provide a padded wheel of platforms that are solid, light and compact. In particular, the Y-shaped structure of the support part ensures a good mechanical strength of the platform while remaining light: it notably makes it possible to withstand centrifugal forces better, which limits the deformations of the part of the vein during the rotation. of the wheel. In addition, the attachment of the platform in a notch of the disc provides a solid attachment, limiting the risk of displacement or stall of the platform during operation of the engine. In particular, this single attachment makes it possible to maintain the platform both against the centrifugal force during the rotation of the wheel and against the gravity when the engine is stopped. It is thus possible to drastically simplify the geometry of the platform and thus obtain significant mass gains.
    [0005] Such attachment also provides ease of assembly and disassembly since the platform can be easily inserted from outside the wheel without having to for example engage hooks in a specific direction. In addition, because of this configuration, the footprint of the platform above the disk tooth is also reduced. It is then possible to bring the upstream end of the vein portion of the tooth of the disc, thus revealing a longer blade length and thereby reducing the hub ratio, which increases the performance of the blower.
    [0006] In some embodiments, the support leg has a bore, the tooth has a first bore opening into said notch, and a retainer is inserted into the bores of the support leg and the tooth to retain the bore. platform. The platform can thus be easily and reliably secured by engaging the retainer through the bores of the support leg and the tooth. In some embodiments, the first bore of the tooth is threaded and the retainer is a screw or a threaded rod. This ensures the locking in position of the retaining member, thus securing the attachment of the platform.
    [0007] In some embodiments, the tooth has a second bore opening on the one hand into the notch opposite the first bore 3021693 4 and on the other hand into a side face of the disk. In this way, it is possible to easily bring the retaining member to the notch, transversely to the support leg. The inventors have further found that such bores provided in the thickness do not compromise the mechanical strength of the tooth and allow on the contrary to achieve substantial gains in mass. In some embodiments, the second bore is smooth, i.e., it is not tapped. In this way, when the retaining member is a screw or a threaded rod, it is possible to push this latter up to the notch quickly, without having to advance it with a screwdriver. In some embodiments, the second bore opens into the upstream face of the disk. The upstream face is indeed easier to access during assembly and disassembly. The second bore could, however, as well lead into the downstream face of the disk. In some embodiments, the support portion has a second Y-shaped portion including a first support arm connected at its end to a third zone of the vein portion, a second support arm connected at its end to a fourth zone of the a vein portion distinct from the third zone, and a support leg extending radially towards the disk from the junction between the first and second support arms; the disc tooth facing said platform is provided with a second notch; and the end of the support leg of the second Y portion is fixed in the second notch 25 of the tooth. In some configurations, this embodiment comprising two Y-shaped portions ensures a better mechanical strength. In addition, it allows the attachment of the platform on the disk at two distinct points, which allows to distribute the efforts. In some embodiments, the second zone of the vein portion coincides with its third zone and the end of the second support arm of the first Y portion is also connected to the end of the first support arm of the second portion. Y. This further strengthens the mechanical strength of the platform. In some embodiments, the tooth has a first bore connecting the two notches, a second bore opening on the one hand into the upstream notch opposite the first bore and on the other hand into an upstream side face of the disk. , and a third bore opening on the one hand in the notch downstream opposite the first bore and on the other hand in a downstream lateral face of the disk. It is thus possible to insert a first retaining member through the upstream face of the disk in order to block the first support leg in the first notch and a second retaining member via the downstream face of the disk in order to block the second support leg. in the second notch. In some embodiments, the first bore is threaded. In some embodiments, the second and third bores are smooth, i.e. they are not tapped. In some embodiments, the vein portion is devoid of any assembly portion at its upstream end and / or at its downstream end. The inventors have indeed found that such assembly portions are rendered superfluous by the binding proposed in this presentation: the design of the platform and its environment is thus further simplified; we also gain more mass. In addition, it reduces the stresses, including bending, generated by the centrifugal forces during rotation. In some embodiments, the bladed wheel is a blower. In some embodiments, the blades have a curvilinear profile. In some embodiments, the grooves of the disk are rectilinear and preferably axial.
    [0008] In some embodiments, the disc teeth are rectilinear and preferably axial. In some embodiments, the vein portion extends from upstream to downstream and from the inside to the outside. In some embodiments, the tooth is devoid of an assembly portion projecting from the outer surface of the tooth. Indeed, the binding proposed in this presentation makes unnecessary such assembly portions, including taking the form of hooks, used in known configurations: thus simplifies the design of the disc and its environment; thus gaining more mass and room for lowering the vein portion.
    [0009] In some embodiments, the platform is a one-piece part. In other embodiments, the support portion is attached to the vein portion.
    [0010] In some embodiments, the platform is of composite material. Such a material makes it possible to gain mass. However, the platform could also be made of metallic material. The present disclosure also relates to a turbomachine fan module comprising, upstream to downstream, an upstream ferrule, a bladed wheel according to any one of the preceding embodiments, and a downstream drum. In some embodiments, the upstream end of the vein portion of at least one platform of the bladed wheel tangents the downstream edge of the upstream ferrule and wherein the downstream end of the vein portion 15 of this tangent platform the upstream edge of the downstream drum. Thus, no assembly is provided between the vein portion and the upstream ferrule on the one hand, the downstream drum on the other hand. In some embodiments, a seal is provided at the interface between the platform and the upstream shell and / or at the interface between the platform and the downstream drum. This ensures aerodynamic continuity between the upstream ferrule and the vein portion and between the vein portion and the downstream drum avoiding possible leaksplatform. The present disclosure also relates to a turbomachine comprising a bladed wheel according to any one of the preceding embodiments or a blower module according to any one of the preceding embodiments. The foregoing and other features and advantages will be apparent from the following detailed description of exemplary embodiments of the proposed device and method. This detailed description refers to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS The accompanying drawings are schematic and are intended primarily to illustrate the principles of the invention.
    [0011] In these drawings, from one figure (FIG) to the other, identical elements (or parts of element) are identified by the same reference signs. In addition, elements (or parts of elements) belonging to different exemplary embodiments but having a similar function 5 are marked in the figures by incremented numerical references of 100, 200, etc. FIG 1 is a sectional plane of a turbomachine according to the invention. FIG 2 is a sectional view of a fan module. FIG 3 is a front view of a fan disk.
    [0012] FIG. 4 is a sectional view of a first example of a platform and disk. FIG 5 is a sectional view of a second example of platform and disk.
    [0013] DETAILED DESCRIPTION OF EMBODIMENT (S) In order to make the invention more concrete, exemplary embodiments of the invention are described in detail below, with reference to the accompanying drawings. It is recalled that the invention is not limited to these examples. 1 shows, in section along a vertical plane passing through its main axis A, a turbofan engine 1 according to the invention. It comprises, from upstream to downstream according to the flow of the air flow, a fan module 2, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, and a turbine low pressure 7.
    [0014] The fan module 2 is shown in greater detail in FIG. 2. It comprises an upstream shell 21, a fan disk 22 and a downstream drum 23 also called a "booster drum". As can be seen in FIG. 3, a plurality of grooves 24 are formed in the outer surface of the fan disk 22: these grooves 24 are rectilinear and extend axially from upstream to downstream along the disk 22. are further regularly distributed around the axis A of the disc 22. In this way, each groove 24 defines with its neighbor a tooth 25 which thus extends also axially from upstream to downstream along the disc 22.
    [0015] The blower module 2 further comprises a plurality of blades 26, each blade 26 having a curvilinear profile being mounted in a respective groove 22 of the blower disk 22. For this purpose, the blade root 26 can have a shape fir or dovetail adapted to the geometry of the grooves 24. The fan module 2 finally comprises a plurality of platforms 30, a platform 30 being provided between each blade 26, so facing each tooth 25 of the fan disk 22. The upstream shell 21 and the downstream drum 23 are connected to the disk 22, the latter being coupled with the low-pressure shaft of the turbojet engine 1. Thus, during operation of the turbojet engine, the upstream shell 21, the 10 fan disk 22, the blades 26 and the downstream drum 23 are integrally rotated by the low-pressure turbine 7. The platforms 30, mounted on the disc 22, are also driven integrally. The structure of these platforms 30 as well as their assembly in the fan module 2 will now be described in detail with reference to FIG. 4. Each platform 30 comprises a vein portion 31, extending the upstream ferrule 21 downstream and the downstream drum 23 upstream, so as to define the flow vein of the air in the blower module 2. Each platform 30 further comprises a support portion 32, Y-shaped, supporting the part The support portion 32 thus comprises a first support arm 34, the distal end of which is directly connected to the vein portion 31 at a first zone 34z, and a second support arm 35, the distal end of which is directly connected to the vein portion 31 at a second zone 35z. The first and second arms meet at a junction 33j. Preferably, the first zone 34z is located in the upstream third 30 of the vein portion 31 while the second zone 35z is located in its downstream third. More preferably, the first zone 34z is located in the upstream quarter of the vein portion 31 while the second zone 35z is located in its downstream quarter. The support portion 32 further includes a support leg 36 extending radially from the juncture 33j to the disc tooth 22. This support leg 36 is a simple, straight, smooth plate without a lateral protrusion 342. . Its distal portion is provided with a through axial bore 36a. Each tooth 25 of the blower disc 22 is provided with a notch 41 made transversely in the thickness of the tooth 25. The position and size of the notch 41 are adapted to receive the distal portion of the support leg 36 of the support portion 32 of a platform 30. A threaded bore 42 is formed in the thickness of the tooth 25 between the notch 41 and the downstream lateral face 22v of the disk 22. This bore 42 is axial and centered. in the thickness of the tooth 25. A smooth bore 43, without threading, is formed in the thickness of the tooth 25 between the notch 41 and the upstream side face 22m of the disc 22. This bore 43 is aligned with the In addition, the bore 36a of the support leg 36 is provided to be aligned with the bores 42 and 43 when the support leg 36 is engaged in the notch 41. attaching the platform 30 to the disk 22, the support leg 36 is engaged in the notch 41 of the tooth 25 of the d isque 22 and then blocks the support leg 36 in position by inserting from the upstream face 22m of the disc 22 a threaded rod 44 through the bores 43 of the tooth, 36 36a of the support leg and 42 of the tooth. The threaded rod 44 is then screwed into the threaded bore 42 so as to prevent it from disengaging. In this position, as can be seen in FIG. 2, the upstream and downstream ends of the vein portion 31 respectively tangent the upstream ferrule 21 and the downstream drum 23 without a portion of one protruding from the 'other. A seal may nevertheless be provided at the interface between the upstream shell 21 and the vein portion 31 on the one hand and between the vein portion 31 on the one hand and the downstream drum 23 on the other hand in order to avoid possible air leakage through these interfaces. A second exemplary embodiment will be described with reference to FIG. 5. This second exemplary embodiment is similar to the preceding one except that the support portion 132 of the platform 130 comprises two Y structures 133 and 133 'at instead of one. Thus, in this example, the first Y portion 133 includes a first support arm 134, the distal end of which is directly connected to the vein portion 131 at a first zone 134z, and a second support arm 135, whose distal end is directly connected to the vein portion 131 at a second zone 135z. The first and second arms 134, 135 meet at a junction 133j. The first Y portion 133 includes a bearing leg 136 extending radially from the juncture 133j to the tooth 125 of the disk 122. The second Y portion 133 'comprises a first support arm 134', the distal end of which is directly connected to the vein portion 131 at the second zone 135z, and a second support arm 135 ', the distal end of which is directly connected to the vein portion 131 at a third zone 136z. The first and second arms 134 ', 135' meet at a junction 133j '. The second Y portion 133 includes a support leg 136 'extending radially from the junction 133j' to the tooth 125 of the disc 122. Thus, the second arm 135 of the first Y portion 133 and the first arm 134 'of the second Y portion 133' meet and are connected in the same zone 135z of the vein portion 131. Preferably, the first zone 134z is located in the upstream third of the vein portion 131, the second zone 135z is located in its median third, and the third zone 136z is located in its downstream third. More preferably, the first zone 134z is located in the upstream quarter of the vein portion 131 and the third zone 136z is located in its downstream quarter. Each tooth 125 of the blower disk 2 is provided with a first notch 141 and a second notch 141 'adapted to receive the distal portion of the abutment legs 136, 136' of the first Y portion 133 and of the second Y portion 133 ', respectively. A tapped bore 142 is formed in the thickness of the tooth 125 between the first notch 141 and the second notch 141 '. A smooth bore 143, without threading, is formed in the thickness of the tooth 125 between the first notch 141 and the upstream side face 122m of the disc 122. Another smooth bore 143 ', without threading, is made in the thickness of the tooth 125 between the second notch 141 'and the downstream side face 122v of the disc 122. The mounting of the platform 130 on the disc 122 is similar to that of the first example except that a first threaded rod 144 is inserted from the upstream to fix the support leg 136 of the first portion Y 133 133 while a second threaded rod 144 'is inserted downstream to fix the support leg 136' of the second Y portion 133 '. The modes or examples of embodiment described in the present description are given for illustrative and not limiting, a person of the trade can easily, in view of this presentation, modify these modes or examples of embodiment, or consider others, all remaining within the scope of the invention. In addition, the various features of these modes or embodiments can be used alone or be combined with each other.
    [0016] When combined, these features may be as described above or differently, the invention not being limited to the specific combinations described herein. In particular, unless otherwise specified, a feature described in connection with a mode or example embodiment may be similarly applied to another embodiment or embodiment.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Turbomachine bladed wheel, comprising a disc (22), adapted to be coupled to a shaft of the turbomachine, whose circumference has a succession of grooves (24) and teeth (25), a plurality of blades (26) mounted in grooves (24) of the disk (22), and at least one platform (30), provided between two blades (26) facing a tooth (25) of the disk (22), having a portion of vein (31) , extending from upstream to downstream, and a support portion (32), characterized in that the support portion (32) has at least one Y-shaped portion comprising a first support arm (34) connected by its end to a first zone (34z) of the vein portion (31), a second support arm (35) connected at its end to a second zone (35z) of the vein portion (31), distinct from the first zone (34z) , and a support leg (36) extending radially towards the disk (22) from the junction (33j) between the first and second support arms (34, 35), in that ue at least the tooth (25) of the disc (22) facing said platform (30) is provided with at least one notch (41), and in that the end of the support leg (36) is fixed in said at least one notch (41) of the tooth (25).
    [0002]
    A bladed wheel according to claim 1, wherein the support leg has a bore (36a), wherein the tooth (25) has a first bore (42) opening into said slot (41), and wherein a member retainer (44) is inserted into the bores (36a, 42) of the support leg (36) and the tooth (25) to retain the platform (30). 302 16 93 13
    [0003]
    The bladed wheel according to claim 2, wherein the first bore (42) of the tooth (25) is threaded and the retaining member is a screw or a threaded rod (44).
    [0004]
    4. A bladed wheel according to claim 2 or 3, wherein the tooth (25) has a second bore (43) opening on the one hand in the notch (41) opposite the first bore (42) and secondly in a lateral face (22m) of the disk (22).
    [0005]
    The bladed wheel according to any one of claims 1 to 4, wherein the support portion (32) has a second Y-shaped portion (133 ') comprising a first support arm (134') connected at its end to a third zone (135z) of the vein portion (131), a second support arm (135 ') connected at its end to a fourth zone (136z) of the vein portion (131) distinct from the third zone (135z), and a support leg (136 ') extending radially towards the disk (122) from the junction (133j') between the first and second support arms (134 ', 135'), wherein the tooth (125) of the disk (122) opposite said platform (130) is provided with a second notch (141 '), and wherein the end of the support leg (136') of the second Y-shaped portion (133 ') is fixed in the second notch (141 ') of the tooth (125).
    [0006]
    6. A bladed wheel according to claim 5, wherein the second zone (135z) of the vein portion (131) coincides with the third zone and wherein the end of the second support arm (135) of the first portion Y (133) is also connected to the end of the first support arm (134 ') of the second Y portion (133').
    [0007]
    7. Bladed wheel according to claim 5 or 6, wherein the tooth (125) has a first bore (142) connecting the two notches (141, 141 '), a second bore (143) opening on the one hand in the upstream notch (141) facing the first bore (142) and secondly in an upstream side face (122m) of the disk (122), and a third bore (143 ') opening on the one hand in the downstream notch (141 ') facing the first bore (142) and secondly in a downstream side face (122v) of the disk (122).
    [0008]
    8. Bladed wheel according to any one of claims 1 to 7, wherein the vein portion (31) is devoid of any assembly portion at its upstream end and / or at its downstream end.
    [0009]
    9. Blower module for a turbomachine, comprising, upstream to downstream, an upstream ferrule (21), a bladed wheel (22, 26, 30) according to any one of the preceding claims, and a downstream drum (23).
    [0010]
    10. Module according to claim 9, wherein the upstream end of the vein portion (31) of at least one platform (30) of the bladed wheel tangents the downstream edge of the upstream ferrule (21) and wherein the the downstream end of the vein portion (31) of this platform (30) tangents the upstream edge of the downstream drum (23).
    [0011]
    11. A turbomachine comprising a bladed wheel (22, 26, 30) according to any one of claims 1 to 8 or a blower module (2) according to claim 9 or 10.
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    同族专利:
    公开号 | 公开日
    FR3021693B1|2019-11-01|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3694104A|1970-10-07|1972-09-26|Garrett Corp|Turbomachinery blade|
    EP2098689A2|2008-03-07|2009-09-09|Rolls-Royce plc|Blade attachment retention device|
    US20130064667A1|2011-09-08|2013-03-14|Christian X. Campbell|Turbine blade and non-integral platform with pin attachment|RU2698534C1|2018-03-06|2019-08-28|Публичное Акционерное Общество "Одк-Сатурн"|Composite fan platform and method of its manufacturing|
    EP3536909A1|2018-03-08|2019-09-11|United Technologies Corporation|Multi-piece fan spacer for a gas turbine engine|
    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|
    法律状态:
    2015-05-07| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-04| PLSC| Search report ready|Effective date: 20151204 |
    2016-05-17| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-13| PLFP| Fee payment|Year of fee payment: 4 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-10| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20200304 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1454844|2014-05-28|
    FR1454844A|FR3021693B1|2014-05-28|2014-05-28|PLATFORM FOR AUBAGEE WHEEL|FR1454844A| FR3021693B1|2014-05-28|2014-05-28|PLATFORM FOR AUBAGEE WHEEL|
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