• 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 an attached fan blade platform on an aeronautical turbomachine fan disk, the assembly comprising: a fan disk (22) comprising at least one tooth (25) having an upstream face ( 33a); at least one platform (30) mounted on the tooth of the fan disk; and a shell (21) mounted upstream on the fan disk, the platform comprising at an upstream end a step (33) having a radial portion (33a) extending through an axial portion (33b) giving the step a longitudinal section substantially L-shaped, the axial portion being intended to provide radial retention of the platform on the disk tooth, the radial portion extending along the upstream face of the disc tooth and comprising an opening (34). ) intended to be axially traversed by a fastening element (21a) ensuring the mounting of the ferrule on the fan disk.
    公开号:FR3033179A1
    申请号:FR1551641
    申请日:2015-02-26
    公开日:2016-09-02
    发明作者:Alexandre Bernard Marie Boisson；Caroline Jacqueline Denise Berdou；Gaillard Thomas Alain De；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 purpose of the present invention is thus to reduce the hub ratio by proposing an assembly of an attached fan blade platform on an aerospace turbomachine fan disk, the assembly comprising: a fan disk comprising at least one tooth having an upstream face; at least one platform mounted on the tooth of the fan disk; and a shell mounted upstream on the fan disk. According to the invention, the platform comprises at an upstream end a step having a radial portion extending by an axial portion giving the step a longitudinal section 15 substantially L-shaped, the axial portion being intended to provide radial retention of the platform on the disk tooth, the radial portion extending along the upstream face of the disc tooth and comprising an opening intended to be axially traversed by a fixing element ensuring the mounting of the ferrule on the fan disk .
    [0004] This assembly, applicable to any type of reported platform for aerospace turbomachine blower (for example a box platform or not) makes it possible to reduce the hub ratio by ensuring the radial retention of the platform upstream of the fan disk tooth. (or in other words, in front of the disc tooth). In fact, the step of the platform, the radial portion of which runs along the upstream face of the disc tooth, then has an axial portion whose role is to ensure the radial retention of the platform. This mounting is possible in particular because the step of the platform has an opening which allows the fixing of the shell on the disk, this fixing being performed without the intermediary of the platform. This avoids imposing additional constraints on the platform or pinch between the ferrule and the disc. In addition, no additional insert is required to provide radial retention of the platform on the upstream tooth, since it is the axial part of the walking platform that allows this retention. This assembly therefore allows a mass saving of 3 03 3 1 79 3 together and greater ease of assembly by reducing the number of mounting steps and inserts. Preferably, the axial portion of the step of the platform is directed upstream being located radially inwardly relative to the ferrule so that the radial retention of the platform is provided by the ferrule. In a variant, the axial part of the step of the platform is directed downstream and is located radially inward with respect to the fan disk so that the radial retention of the platform is ensured by the fan disk. According to one embodiment of the invention, the opening is a notch made in the radial portion of the step extending on its axial portion and opening at one end thereof. This configuration allows to leave a degree of freedom including radial and / or tangential to the platform. According to another embodiment of the invention, the opening is a hole made in the radial part of the step. This configuration allows, unlike that comprising a notch, reduce the possible movements of the platform once the ferrule is fixed on the disc. 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, wherein 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. 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. FIG. 3 is a perspective view of the upstream part of a platform forming part of an assembly according to one embodiment of the invention; FIGS. 4A and 4B are longitudinal sectional views along the plane; IV of Figure 3 of an assembly of a platform on a fan disk, - Figures 5A and 5B are longitudinal sectional views along the plane V of Figure 3 of an assembly of a platform on a disk 6 is an enlarged view of a longitudinal section of an assembly of a platform on a fan disk according to another embodiment of the invention, and FIG. perspective of a platform according to yet another embodiment of the invention.
    [0005] In this disclosure, the terms "longitudinal", "transversal", "lower", "superior" and their derivatives are defined with respect 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. Also, unless otherwise indicated, the same reference numerals 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 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 are formed at its outer periphery. These grooves 24 are rectilinear and extend axially from upstream to downstream along the length of 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.
    [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, 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 for use in an assembly according to one embodiment of the invention is shown in perspective 30 in Figure 3 at its upstream portion. The platform 30 takes the form of a box with a vein wall 31, forming the upper or outer face of the platform 30 and having an inclined profile, and a bottom wall 32 (FIGS. 4A, 5A) which allows the platform 30 to rest on the tooth 25 of the disc 22 when the turbomachine is stopped.
    [0007] A step 33 having a substantially L-shaped longitudinal section is also present at the upstream end of the platform 303. The step 33 includes a radial portion 33a extending through an axial portion 33b for providing a radial retention of the platform 30 on the tooth of the disc 22. In addition, the step 33 comprises an opening here taking the form of a notch 34 formed in the radial portion 33a and extending on the axial portion 33b leading to one end of it. Alternatively, the opening may take the form of a hole 34 "made in the step 33 of the platform 30" (FIG. 7), depending on whether it is desired to leave a degree of radial and tangential freedom to the platform, or no.
    [0008] An assembly employing the platform 30 presented previously with reference to FIG. 3 will now be described with reference to FIGS. 4A, 4B, 5A and 5B. These figures illustrate in more detail a blower 2 comprising an assembly according to one embodiment of the invention.
    [0009] Figures 4A and 4B show a longitudinal sectional view of the blower 2 along the plane IV of Figure 3 at a solid portion of the step 33 of the platform 30; while FIGS. 5A and 513 show a longitudinal sectional view of the fan 2 along the plane V of FIG. 3 at the notch 34 of the platform 30.
    [0010] In FIG. 4A it is possible to see in particular a blower 2 comprising: an upstream shell 21, the fan disk 22, a downstream drum 23 (also called a "booster" drum) provided with a retaining flange 23a designed to cooperate with a assembly step 31a of the platform 30 downstream, and an inlet cone 27 whose function is to deflect the flow of air entering the turbomachine to the blades 26 of the fan. The downstream drum 23 is fixed on the fan disk 22 by means of fasteners 23b. The shell is attached to the fan disk 22 by means of fasteners 21a (visible in FIGS. 5A and 5B) which pass through the notch 34 of the platform 30, and the inlet cone 27 is fixed on the ferrule 21 through fasteners 27a (visible in Figures 4A and 4B). 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, the fan cone 27 and the downstream drum 23 are driven in rotation 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 jointly in rotation.
    [0011] In the enlarged view of FIG. 4B, it can be seen that the radial portion 33a of the step 33 of the platform 30 runs along an upstream face 22a of the tooth 25 of the disc 22, and is extended by the axial portion 33h which is directed in this configuration, the radial retention of the platform 30 on the tooth 25 of the disk 22 is provided upstream by the ferrule 21. In a variant, as can be seen on the platform 30 'of FIG. 6, the axial part 33b' of the step 33 'can be directed downstream and situated inside with respect to the disk 22. In this way, the platform 30 takes a part of the disk 22 in vice. In this configuration, the radial retention of the platform 30 'on the tooth 25 of the disk 22 is provided upstream by the disk 22 itself. Thus, the radial retention of the platforms 30, 30 ', 30 "upstream can be carried out in front of the disk 22 by the shell 21 or by the disk 22 itself, which makes it possible to reduce the internal radius RI with respect to a 20 platform whose upstream retention is performed above the disk tooth, and therefore to reduce the ratio RI / RE hub of the fan 2 according to the invention. This not only limits the reported platforms comprising a box and may particularly concern box-less platforms, and other combinations of the features of the present invention are possible.
    权利要求:
    Claims (6)
    [0001]
    REVENDICATIONS1. A blower blade reported platform assembly on an aerospace turbomachine blower disc, the assembly comprising: a blower disc (22) comprising at least one tooth (25) having an upstream face (33a); at least one platform (30; 30 '; 30 ") mounted on the tooth of the fan disk; and a ferrule (21) mounted upstream on the fan disk, characterized in that the platform comprises at one end upstream a step (33) having a radial portion (33a) extending through an axial portion (33b) imparting to the step a longitudinal section substantially L-shaped, the axial portion being intended to provide radial retention of the platform on the tooth of the disk, the radial portion extending along the upstream face of the tooth of the disk and comprising an opening (34; 34 ") intended to be axially traversed by a fixing element (21a) ensuring the mounting of the ferrule on the blower disc. 20
    [0002]
    2. Assembly according to claim 1, characterized in that the axial portion (33b) of the step (33) of the platform (30; 30 ") is directed upstream by being located radially inward with respect to the shell (21) so that the radial retention of the platform is provided by the ferrule.
    [0003]
    3. An assembly according to claim 1, characterized in that the axial portion (33b) of the step (33) of the platform (30 ') is directed downstream being located radially inwardly relative to the disc 30 blower (22) so that the radial retention of the platform is provided by the fan disk.
    [0004]
    4. Assembly according to any one of claims 1 to 3, characterized in that the opening (34) is a notch formed in the radial portion (33a) of the step (33) extending on its axial portion (33b ) and opening at one end thereof. 303 3 1 7 9 9
    [0005]
    5. Assembly according to any one of claims 1 to 3, wherein the opening (34 ") is a hole in the radial portion (33a) of the step (33).
    [0006]
    Aeronautical turbomachine blower (2) comprising: an assembly of a platform on a blower disc according to any one of claims 1 to 5 wherein the blower disc (22) has at least two teeth (25) defining 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:
    公开号 | 公开日 | 专利标题
    EP1972757B1|2012-07-18|Rotor assembly of a turbomachine fan
    EP3320181B1|2019-05-22|Rotor assembly of an aeronotical turbine engine comprising an inter-blade platform of a fan
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    FR3033179A1|2016-09-02|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK
    FR3010442A1|2015-03-13|REDUCED MONOBLOC DRAWING DISK IN WAVE FOOT, PREFERABLY FOR AIRCRAFT TURBOMACHINE BLOWER
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    FR3065759A1|2018-11-02|CENTRIFUGAL ROLLER FOR TURBOMACHINE
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    FR2994718A1|2014-02-28|Casing for supporting series of fixed vanes in high pressure axial compressor of turbojet of aircraft, has blades, where radial external end of blades passes through whole of opposite areas of casing devoid of spiral grooves
    BE1026199A1|2019-11-05|EXTERIOR VIROLE IN TWO PARTS
    FR3085992A1|2020-03-20|TURBINE MOBILE WHEEL BLADE HAVING A CURVILINATED SHAPE
    EP3433469A1|2019-01-30|Fan assembly, disk and platform
    同族专利:
    公开号 | 公开日
    US10094390B2|2018-10-09|
    US20160252102A1|2016-09-01|
    GB2538834B|2020-04-08|
    GB201603037D0|2016-04-06|
    FR3033179B1|2018-07-27|
    GB2538834A|2016-11-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2014143268A1|2013-03-12|2014-09-18|United Technologies Corporation|T-shaped platform leading edge anti-rotation tabs|FR3048997A1|2016-03-21|2017-09-22|Snecma|DRAFT PLATFORM AND AERONAUTICAL TURBOMACHINE BLOWER DISK|
    FR3108149A1|2020-03-11|2021-09-17|Safran Aircraft Engines|BLOWER MODULE FOR AN AIRCRAFT TURBOMACHINE|US6416280B1|2000-11-27|2002-07-09|General Electric Company|One piece spinner|
    US6447250B1|2000-11-27|2002-09-10|General Electric Company|Non-integral fan platform|
    US8777576B2|2011-08-22|2014-07-15|General Electric Company|Metallic fan blade platform|
    FR2986580B1|2012-02-08|2014-02-28|Safran|ROTOR REVOLUTION PIECE OF AERONAUTICAL TURBOMACHINE|
    US9759226B2|2013-02-15|2017-09-12|United Technologies Corporation|Low profile fan platform attachment|CN111852906B|2019-04-28|2022-02-22|中国航发商用航空发动机有限责任公司|Aircraft engine fan device and aircraft engine|
    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
    FR1551641A|FR3033179B1|2015-02-26|2015-02-26|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|
    FR1551641|2015-02-26|FR1551641A| FR3033179B1|2015-02-26|2015-02-26|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|
    GB1603037.1A| GB2538834B|2015-02-26|2016-02-22|A rotary assembly for an aviation turbine engine, the assembly comprising a separate fan blade platform mounted on a fan disk|
    US15/051,106| US10094390B2|2015-02-26|2016-02-23|Rotary assembly for an aviation turbine engine, the assembly comprising a separate fan blade platform mounted on a fan disk|
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