WO2022243628A1 - Plateforme de roue aubagée - Google Patents
Plateforme de roue aubagée Download PDFInfo
- Publication number
- WO2022243628A1 WO2022243628A1 PCT/FR2022/050921 FR2022050921W WO2022243628A1 WO 2022243628 A1 WO2022243628 A1 WO 2022243628A1 FR 2022050921 W FR2022050921 W FR 2022050921W WO 2022243628 A1 WO2022243628 A1 WO 2022243628A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- platform
- upstream
- disc
- downstream
- retention means
- Prior art date
Links
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 38
- 230000014759 maintenance of location Effects 0.000 claims abstract description 26
- 239000003351 stiffener Substances 0.000 claims abstract description 11
- 210000003462 vein Anatomy 0.000 claims description 24
- 239000002131 composite material Substances 0.000 claims description 8
- 238000000605 extraction Methods 0.000 description 4
- 230000010354 integration Effects 0.000 description 4
- 238000013519 translation Methods 0.000 description 4
- 230000014616 translation Effects 0.000 description 4
- 230000000717 retained effect Effects 0.000 description 3
- 230000000875 corresponding effect Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000008485 antagonism Effects 0.000 description 1
- 230000006399 behavior Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 210000003456 pulmonary alveoli Anatomy 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000037221 weight management Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/31—Retaining bolts or nuts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to the field of bladed wheel platforms.
- a low pressure compressor can be composed of a bladed fan wheel X which comprises a casing, a fan disc I, several blades and their retention systems, several platforms III , and an upstream shell IV.
- the platform is an integral part of the bladed wheel of the fan constituting the first mobile wheel stage. It must perform the following functions:
- the performance and integration requirements translate into good control of the airtightness of the blade near its root retained in the disc.
- This tightness is directly controlled by the capacity of the platform to be associated with the blade near its foot, and this at any point of operation. Up to a certain clearance, it is possible to fill with the use of a gasket. From a certain clearance, it is difficult to ensure a seal.
- the platform is screwed onto radial extensions of the disc (as is the case for the platform described in document US 20140186187).
- the platform is retained by a plurality of hooks carried by the disc.
- the invention proposes a bladed wheel platform, comprising a vein wall extending in an axial direction by having an upstream end and a downstream end, and comprising two axial stiffeners.
- the platform comprises radial retention means positioned at the upstream end and at the downstream end of the stream wall, the radial retention means being adapted to each define a slide connection with a corresponding shroud of the bladed wheel and that it comprises tangential retention means adapted to define a sliding pivot connection between the platform and a disk of the bladed wheel.
- the tangential retention means may comprise a pin and a lug having a hole adapted to receive the pin, so that the assembly of the lug and the pin forms a sliding pivot connection.
- the tab can be fixed to the vein and the pin can be adapted to be fixed to the disk of the bladed wheel.
- the radial retention means may comprise an upstream circumferential bearing surface and a downstream circumferential bearing surface, which are adapted to be engaged respectively in an upstream shroud and a corresponding downstream shroud of the bladed wheel.
- the vein and the stiffeners can be made of composite materials.
- the invention relates to an assembly of a bladed wheel disc and a platform, in which the disc receives the platform and has a fitting in which is fixed the pin adapted to be engaged in a sliding pivot connection in the platform leg.
- the disk can receive the platform and can comprise at least one downstream ferrule adapted to receive the downstream circumferential bearing and at least one upstream ferrule adapted to receive the upstream circumferential bearing.
- the invention relates to a turbomachine comprising at least one assembly according to the invention.
- the invention relates to an aircraft comprising at least one turbomachine according to the invention.
- FIG. 1 is a schematic representation of a bladed wheel of the prior art.
- FIG. 2 is a perspective representation of the assembly of a platform and a disc according to the invention.
- FIG. 3 is a detailed perspective representation of the assembly of an upstream circumferential bearing surface and an upstream shell according to the invention.
- FIG. 4 is a detailed perspective representation of the assembly of a downstream circumferential seat and a downstream shroud according to the invention.
- FIG. 5 is a detailed perspective representation of the assembly of a pin and a leg of the platform according to the invention.
- FIG. 6 is a representation in perspective and in partial section of the assembly of the pin and the leg of Figure 5.
- FIG. 7 is a schematic perspective representation of the extraction of a platform according to the invention.
- FIG. 8 is a representation of the connection in a pin and a leg according to a second embodiment of the invention.
- the invention is positioned in a bladed wheel 1 of a fan. Typically this may be a low pressure compressor fan.
- the bladed wheel 1 comprises a disk 2 on which blades 4 are fixed.
- Platforms 6 are at the interface between the blades 4 and the disk 2 in order in particular to create, via an upper face of the platform, a flow on the inside of vein between the blades near their root which is held in the disc in a conventional alveolus of the disc.
- the invention relates to the platforms 6 and the disk 2, and more particularly to the connection between the platforms 6 and the disk 2.
- the invention proposes a platform 6 of bladed wheel 1.
- the platform 6 comprises a vein wall 8 which extends in an axial direction.
- the stream wall 8 has its so-called upper face, opposite the disk, determining a surface shape which promotes fluid flow in a generally longitudinal direction between the vanes on the inner side of the stream.
- the duct wall 8 extends in an axial direction between an upstream region and a duct wall 8 makes it possible to promote the flow of air in the fan between the upstream and the downstream of the wheel bladed 1.
- the vein wall 8 is made of composite material.
- This choice of material makes it possible to have a vein wall 8 with optimal curvature.
- the choice of a vein wall 8 made of composite material makes it possible to conform the vein 8 according to a desired surface geometry (as opposed to a sheet which is more difficult to shape).
- the vein wall made of composite material is favorable to the lesser aggressiveness of this wall with regard to the blades in the event of a major impact on the latter.
- the platform 6 comprises two axial stiffeners 10.
- the stiffeners 10 are positioned under the wall of the section 8 to stiffen it.
- the stiffeners 10 are located between the disc 2 and the vein wall 8.
- the architecture of the platform 6 with a vein 8 stiffened by axial stiffeners 10 very advantageously makes it possible to have a mechanically resistant structure which offers an optimal surface for the flow of air flow.
- stiffeners 10 can be made of composite material.
- the platform 6 comprises on the one hand radial retention means and on the other hand tangential retention means.
- the radial retention means are arranged upstream 12 and downstream 14 of the platform 6.
- the platform 6 comprises on the one hand radial retention means arranged upstream 12 and on the other hand radial retention means arranged downstream 14.
- the radial retention means comprise an upstream circumferential bearing surface 16, positioned at an upstream end 12 of the platform 6.
- circumferential bearing it is understood a circumferential rib, that is to say in the shape of an arc of a circle.
- the upstream circumferential bearing 16 is adapted to be engaged in a circumferential groove of an upstream shroud 18.
- the connection between the upstream circumferential bearing 16 and the upstream shroud 18 is preferably a slide-type connection.
- upstream shroud axially retains the upstream of the platform to block the platform in this direction.
- translation movements in the tangential direction are permitted.
- the radial retention means comprise a downstream circumferential bearing surface 20, positioned at a downstream end 14 of the platform.
- circumferential bearing it is understood a circumferential rib, that is to say in the shape of an arc of a circle.
- the downstream circumferential bearing 20 is adapted to be engaged in a circumferential groove of a downstream shroud 22.
- the connection between the downstream circumferential bearing 20 and the shroud downstream 22 is preferably a slide-type connection.
- the connection between the downstream circumferential bearing surface 20 and the downstream shroud 22 limits all the degrees of freedom in rotation and prohibits translations in the radial direction.
- the downstream shroud axially retains the downstream of the platform to block the platform in this direction.
- translational movements in the axial direction are permitted on the downstream side when the upstream shroud is removed, for assembly and disassembly operations. They allow in this case the introduction and extraction of the downstream circumferential bearing 20 in the downstream shroud 22. In addition, translational movements in the tangential direction are allowed.
- the assembly by circumferential seats, combined with the realization of a composite material vein wall allows to have a very low hub ratio while minimizing the mass of the bladed wheel.
- Platform 6 also includes tangential retention means.
- the tangential retention means are adapted to define a sliding pivot connection between the platform 6 and the disc 2 of the bladed wheel 1.
- the tangential retention means comprise a lug 26 and a pin 28.
- the lug 26 has a hole adapted to receive the pin 28 and thus form a sliding pivot connection with the pin 28.
- tab 26 is attached to vein wall 8 and pin 28 is attached to disc 2.
- the lug 26 can be made of metal and be screwed on the underside of the vein wall
- the lug 26 has a portion 26a for attachment to the vein wall 8 of the platform 6 and a connection portion 26b to the disc having the bore 30, this portion being intended to be in connection with a fitting 36.
- the attachment portion and the portion having the bore 30 are secant.
- the fixing portion 26a comprises a hooking plate 27a intended to be pressed against and screwed against the vein wall 8.
- the hooking plate 27a can be screwed to the vein wall 8 by two screws 81.
- the fixing portion 26a comprises two half-arch sides 27b. The half-arch sidewalls make it possible to mechanically reinforce the connection between the fixing portion 26a and the connecting portion 26b.
- each flank 27b has a curved edge forming a continuous and progressive connection with the connecting portion 26b.
- This arrangement makes it possible to optimize the mechanical strength of the lug 26, in particular by maximizing the resistance to bending forces between the fixing portion 26a and the connecting portion 26b.
- the pivot-sliding type connection is a particularly advantageous arrangement of the invention which makes it possible to ensure blocking in the tangential direction while allowing movement in the axial direction. As will be developed below, this arrangement is particularly advantageous in the event of, for example, an impact (such as a bird) on the bladed wheel 1).
- the invention proposes a disk 2 of bladed wheel 1, adapted to cooperate with a platform 6 according to the invention.
- the disc 2 has a plurality of fittings 36 each adapted to receive a pin 28, the fittings 36 being radial protuberances.
- fitting 36 is meant a tab or a metal tab extending in a radial direction and having a bore 30 adapted to receive a pin 28.
- the fitting 36 has a support face connected with the connecting portion 26b of the tab
- the support face of the fitting 36 is opposite a support face of the connecting portion 26b, the two support faces being positioned in a radial plane.
- the bearing surfaces of the fitting 36 and of the connecting portion 26b are in a plane substantially perpendicular to the axial direction of rotation of the disc 2 and of the wheel bladed 1.
- the fixing portion 26a of the lug 26 and the connecting portion 26b having the bore 30 intersect at an angle substantially different from 90 degrees and defined according to the desired inclination for the vein 8 .
- the two bearing surfaces of the fitting 36 and of the connecting portion 26b are positioned in a plane inclined with respect to a radial plane.
- the bearing surfaces are not in a plane substantially perpendicular to the axial direction of rotation of the disk 2 and of the bladed wheel 1.
- the portion of attachment 26a of tab 26 and connecting portion 26b having bore 30 intersect at an angle substantially equal to 90 degrees (orthogonal).
- the orthogonal leg 26 facilitates the introduction of tools allowing the leg 26 to be screwed to the vein wall 8.
- the pin 28 is fixed to the fitting 36.
- it is linked to the fitting by an embedding-type connection, that is to say that all the degrees of freedom of the piece 28 are blocked.
- the pin 28 is screwed to the fitting 36, as shown in Figures 5 and 6.
- the system coupled by a single pin 28 in a sliding pivot connection and circumferential spans releases degrees of freedom compared to a multi-pin system and simplifies the platform layouts 6 for avoid the risk of damage to the platform 6 during assembly and operation.
- the installation of the platform 6 is therefore made easier by the release of these degrees of freedom while maintaining the main function of the pin 28 which is to take up the centrifugal forces.
- the longitudinal positioning of the fitting 36, substantially mid-length of the disc, and the longitudinal positioning of the tab 26 substantially mid-length of the platform reduces the risk of deformation of the platform 6 under the effect of the centrifugal forces that the platform 6 undergoes during operation.
- the installation of the platform 6 according to the invention involves a shorter assembly kinematics than for the platforms of the prior art, which reduces the clearances necessary, and therefore reinforces the mechanical structure of the connection between the platform 6 and disk 2. It is specified that the clearances required are directly correlated to the displacement required during assembly/disassembly. In the case of the invention, the assembly/disassembly kinematics are reduced, the clearances are therefore reduced accordingly.
- the invention relates to an assembly of a disc 2 of a bladed wheel 1 according to the invention and a platform 6 according to the invention, in which the disc 2 receives the platform 6.
- the invention relates to a turbomachine comprising at least one assembly according to the invention.
- the invention relates to an aircraft comprising at least one turbomachine according to the invention.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202280036285.7A CN117355663A (zh) | 2021-05-18 | 2022-05-13 | 用于风扇组件的平台 |
EP22730582.8A EP4341533A1 (fr) | 2021-05-18 | 2022-05-13 | Plateforme de roue aubagée |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2105184A FR3123088B1 (fr) | 2021-05-18 | 2021-05-18 | Plateforme de roue aubagée |
FRFR2105184 | 2021-05-18 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2022243628A1 true WO2022243628A1 (fr) | 2022-11-24 |
Family
ID=77226871
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2022/050921 WO2022243628A1 (fr) | 2021-05-18 | 2022-05-13 | Plateforme de roue aubagée |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP4341533A1 (fr) |
CN (1) | CN117355663A (fr) |
FR (1) | FR3123088B1 (fr) |
WO (1) | WO2022243628A1 (fr) |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1967695A1 (fr) * | 2007-02-28 | 2008-09-10 | Snecma | Soufflante de turbomachine |
FR2992676A1 (fr) | 2012-06-29 | 2014-01-03 | Snecma | Plateforme inter-aubes pour une soufflante, rotor d'une soufflante et procede de fabrication associe |
US20140186187A1 (en) | 2012-12-31 | 2014-07-03 | General Electric Company | Non-integral fan blade platform |
FR3018473A1 (fr) * | 2014-03-17 | 2015-09-18 | Snecma | Procede de fabrication d'une plate-forme d'aube en materiau composite a joints integres pour soufflante de turbomachine |
FR3029563A1 (fr) | 2014-12-08 | 2016-06-10 | Snecma | Plateforme a faible rapport de moyeu |
WO2017209963A1 (fr) * | 2016-06-02 | 2017-12-07 | General Electric Company | Plate-forme de pales de ventilateur à écarteur de charge conique destinée à un assemblage boulonné composite |
WO2020128397A1 (fr) * | 2018-12-21 | 2020-06-25 | Safran | Preforme avec un renfort fibreux tisse en une seule piece pour plateforme inter aube |
-
2021
- 2021-05-18 FR FR2105184A patent/FR3123088B1/fr active Active
-
2022
- 2022-05-13 CN CN202280036285.7A patent/CN117355663A/zh active Pending
- 2022-05-13 EP EP22730582.8A patent/EP4341533A1/fr active Pending
- 2022-05-13 WO PCT/FR2022/050921 patent/WO2022243628A1/fr active Application Filing
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1967695A1 (fr) * | 2007-02-28 | 2008-09-10 | Snecma | Soufflante de turbomachine |
FR2992676A1 (fr) | 2012-06-29 | 2014-01-03 | Snecma | Plateforme inter-aubes pour une soufflante, rotor d'une soufflante et procede de fabrication associe |
US20140186187A1 (en) | 2012-12-31 | 2014-07-03 | General Electric Company | Non-integral fan blade platform |
FR3018473A1 (fr) * | 2014-03-17 | 2015-09-18 | Snecma | Procede de fabrication d'une plate-forme d'aube en materiau composite a joints integres pour soufflante de turbomachine |
FR3029563A1 (fr) | 2014-12-08 | 2016-06-10 | Snecma | Plateforme a faible rapport de moyeu |
WO2017209963A1 (fr) * | 2016-06-02 | 2017-12-07 | General Electric Company | Plate-forme de pales de ventilateur à écarteur de charge conique destinée à un assemblage boulonné composite |
WO2020128397A1 (fr) * | 2018-12-21 | 2020-06-25 | Safran | Preforme avec un renfort fibreux tisse en une seule piece pour plateforme inter aube |
Also Published As
Publication number | Publication date |
---|---|
EP4341533A1 (fr) | 2024-03-27 |
FR3123088A1 (fr) | 2022-11-25 |
CN117355663A (zh) | 2024-01-05 |
FR3123088B1 (fr) | 2023-11-24 |
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