• 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 comprising: - a moving blade (100) for a turbomachine comprising a heel (130), - a removable part (300) comprising an anti-wear material, configured to be fixed in a removable manner at a heel edge (130) to limit heel wear (130).
    公开号:FR3066780A1
    申请号:FR1754601
    申请日:2017-05-24
    公开日:2018-11-30
    发明作者:Vijeay PATEL；Pragash DOUGLAS；Bruno Guy Andre Emile Lievoux Quentin；Pauline NAMVONG
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Anti-wear removable piece for dawn heel
    GENERAL TECHNICAL FIELD The invention relates to the installation of anti-wear material on blade heels in an aircraft turbomachine.
    The vanes can be turbine or distributor vanes. The invention relates more particularly to the mobile blading heels of a low-pressure turbine.
    STATE OF THE ART
    In a turbomachine, the turbine recovers part of the energy from the combustion of gases for the operation of the blower, the compressor and the accessories. One of the constituent parts of the turbine is the rotor.
    Due to the mechanical and vibrational stresses, these parts need a material of higher hardness in order to provide better vibration damping and better tolerance to friction for the areas of the heel in contact.
    For this, a known method consists in depositing, after manufacture of the blade, an anti-wear material at certain areas of the heel by brazing or loading. The document FR3001758 describes a heel architecture adapted for this and describes the installation of the anti-wear material.
    However, this process, which is called “stellitage”, from the commercial name of the anti-wear material generally used, is complicated and generates cracks, zones of weakness at the interface between the two materials and material shortages.
    In addition, these areas, which wear out, must be repaired regularly. Typically, we remove the rest of the anti-wear material and put a new layer.
    Another known method consists in placing an insert in the blade which, after heating, forms an integral part of the blade. It nevertheless generates difficulties in interfacing, in particular due to the bi-material nature of the blade.
    There is thus a need for improvement to simplify the “stellitage” of the heel of a dawn.
    PRESENTATION OF THE INVENTION The invention thus proposes an assembly comprising: - a movable blade for a turbomachine comprising a heel, - a removable part comprising an anti-wear material, configured to be removably fixed at an edge of the heel to limit wear on the heel.
    In this way, the operations of "stellitage" are faster and simpler, since it suffices to replace the removable part.
    The heel may include a platform having a first edge on the lower surface side of the blade and a second edge on the upper surface side of the blade, in which the removable part is configured to be fixed to one of the two edges.
    The removable part can then have at least one end folded in the form of a hook for sandwiching a portion of the platform at said edge.
    The removable part, when fixed on the blade, can extend from the first edge to the second edge.
    The removable part may have two ends folded in the form of a hook for sandwiching a portion of the first edge and a portion of the second edge.
    The two edges may have respective protruding and recessed shapes, in order to allow an assembly of two adjacent vanes, and in which the removable part, when installed, covers the protrusion and / or the recess.
    The heel may include two sealing wipers extending from the platform and in which, when installed, the removable part is located between the two wipers.
    The removable part can be made of said anti-wear material.
    The removable part may comprise a coating of said anti-wear material.
    The removable part can be deformable, in order to allow it to be fixed on the heel of the blade, preferably by elastic deformation. The invention also relates to a removable part as defined above and which is intended to be used on a blade stub. The invention also relates to a turbine comprising a plurality of assemblies as described above, in which, for two blades successively arranged, the respective removable parts are in contact at the level of the anti-wear material.
    Finally, the invention relates to a stellitage process using an assembly as described above, comprising a step of mounting the removable part on the heel of the blade by deforming said removable part. The method can also comprise an anterior or posterior step of dismantling the removable part already mounted on the heel, by deforming said removable part.
    PRESENTATION OF THE FIGURES Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and which should be read with reference to the appended drawings, in which: - Figure 1 represents a turbine blade as currently existing, - Figures 2 to 7 illustrate different views of a particular embodiment of the invention mounted on a turbine blade heel.
    DETAILED DESCRIPTION
    The detailed description will be made on a turbine engine turbine blade, in particular for an aircraft.
    FIG. 1 illustrates a turbine blade 100. This conventionally comprises three parts: a blade 110 which includes a lower surface 112 and an upper surface 114, a foot 120 at a proximal end of the blade 110 and a heel 130 at an opposite end , called distal. The terms “distal” and “proximal” are defined with respect to a longitudinal axis along which the turbomachine extends. This longitudinal axis corresponds to the main axis of rotation of the various major components of the turbomachine.
    The blade 110 is the part which receives the air flow coming from an air stream (primary stream for a turbomachine turbine with double flow for example). When installed, the blade 110 extends radially outward relative to the longitudinal axis of the turbomachine. The extension direction of the blade 110 substantially defines a direction Z.
    The foot 120 is fixed to a hub such as a disc of the rotor of the turbomachine. The disc allows the blade to rotate around the longitudinal axis of the turbomachine. The foot will not be described further.
    The heel 130 comprises a platform 200 having a first edge 210, on the pressure side 112, and a second edge 220, on the suction side 114. When several blades are fixed on a rotor disc, their respective heel 130 are arranged edge to edge. so as to form a rotary crown delimiting a surface of revolution around the main axis of the machine, in particular using the respective platforms 200. The function of this crown is in particular to delimit an external surface of a gas flow stream and to limit leaks.
    The platform 200 substantially defines the direction Y. The direction Y is the tangential direction of the aforementioned crown. The X direction is orthogonal to the Y and Z directions.
    Thus, when a plurality of blades 100 is installed, the first edge 210 of a first blade 100 is opposite the second edge 220 of a second blade 100.
    The edges 210, 220 have complementary shapes. For example, the first edge 210 on the lower side 112 has a recessed shape and the second edge 220 on the upper side 114 has a protruding shape, configured to be received in the recessed shape of the first edge 210 of the adjacent blade along the circumference of the turbomachine. The projection can form a V, called positive V, and the withdrawal can form a V, called negative V.
    In particular, the thickness of the platform 200 decreases towards the top of the V (for the two V).
    At the junction between two blades 100, to avoid wear and better withstand the forces caused by the contacts, the heel 130 is reinforced with an anti-wear material. For this, a removable part 300 is used comprising an anti-wear material. The removable part 300 can thus be fixed and removed from the heel 130 of the blade 100.
    In one embodiment (not illustrated in the figures), the removable part 300 only protects a single edge 210 or 220 from the blade 100. Another removable part is then provided to protect the other edge 220 or 210.
    In another embodiment, illustrated in FIGS. 2 to 7, the removable piece 300 extends from the first edge 210 to the second edge 220, that is to say that the same removable piece 300 protects the heel 130 from the 'blade for contacts with the two adjacent blades, on both sides.
    The removable part 300 extends beyond the edge 210 or 220 which it protects, in order to protect said edge.
    In order to be kept attached to the heel 130, the removable part 300 may have a folded end 310, which forms a hook, and which sandwiches the platform at the edge 210. Preferably, the other end 320 of the part removable 300 is also folded back to form a hook which sandwiches platform 200 at the other edge 220.
    Thanks to the hook, the movement in direction Z is blocked. Indeed, during the rotation of the turbine, the centrifugal force tends to eject the removable part radially outwards. The folded end 310 is then pressed against the face of the platform 200 which is on the side of the blade 110.
    The folded portion measures between a few millimeters and a few centimeters. It must be short enough so as not to touch the blade, otherwise the positioning of the removable part 300 is impossible, and long enough to correctly hold the removable part 300.
    A central portion 330 is defined in the removable part 300, between the two ends 310, 320. The central portion 330 is in contact, or almost in contact, with the face of the platform 200 which is on the side opposite to the blade 110.
    The central portion 330 is typically a cylinder portion, that is to say that it is generated by a plurality of parallel lines, in the direction Y.
    There is also defined at the removable part 300 a connection part 315, respectively 325, which connects the central portion 330 to the first folded end 310, respectively the second folded end 320. The connection part 315, 325 therefore has a corresponding length substantially to the thickness of the platform 200 at the end 310, 320 where the removable part 300 attaches. As the thickness of the platform 200 varies along the ends 310, 320, the length of the connection portion 315, 325 varies similarly.
    The hook 310, 320 or more exactly the connection portion 315, 325 blocks the movement of the removable part in the direction Y while being in abutment against the thickness of the platform 200.
    The removable part 300 has a shape which is substantially identical to that of the heel at its ends, because these ends must conform to the shape of the edges 210, 220. As soon as the edges 210 and 220 are not straight in the direction X, the fact that the removable part 300 has similar shapes makes it possible to block the displacement in X on the heel 130.
    Thus, the removable part 300 is blocked in the three directions X, Y and Z.
    In correspondence with the shape of the platform, at the first end 310, the removable part 300 ends in projection and at the second end 320, opposite to the first end 310, the removable part 300 ends in withdrawal. In the same way as for edges 210, 220, one can define a positive V at the level of the first end 310, which cooperates with the positive V of one of the two edges 210, 220, and a negative V at the level of the second end 320, which cooperates with the negative V on the other of the two edges 210, 220.
    The establishment of the removable part 300 is preferably done by deformation of said part. This eliminates the need for other tools or a removable part made of several parts.
    In one embodiment, the deformation takes place in an elastic manner. Thanks to the elongated shape of the removable part 300, in particular when it covers the two edges 210, 220, it inherently has elastic flexibility. This allows the part 300 to be deformed in order to be able to insert the folded ends 310, 320 at the edges 210, 220. This is thus known as clipping or snapping.
    In another embodiment, the deformation takes place in a plastic manner. An operator permanently deforms the removable part 300 so that it is held on the heel 130. It suffices to deform it again to remove it later.
    Once in place, the removable part covers part of the heel 130, like a cover or a cover.
    The removable part is relatively fine. Its thickness can preferably vary between 0.3 mm and 10 mm. However, we will favor a low thickness at the central portion 206 so as not to interfere with the design and assembly of the blades.
    The anti-wear material must be located, once the removable part 300 is placed on the heel 130, at the level of the contact zones between two adjacent blades. This means that the connection portions 315, 325 comprise said anti-wear material.
    Several alternatives are possible for the production of the removable part.
    In one embodiment, the removable part 300 is made of the anti-wear material itself. The removable part 300 is therefore single-material.
    In one embodiment, the removable part 300 is made of a suitable material, for example chosen for its elasticity, on which the anti-wear material is deposited in the zones which will be at the edges 210, 220. The removable part 300 is therefore bi-material, or more, which limits the amount of anti-wear material to be used.
    The anti-wear material can be a specific alloy of high hardness. For example, the antiwear material can be a cobalt base alloy, for example an alloy of cobalt, tungsten chromium and carbon, for example such an alloy of the type of those sold under the brand "Stellite", having good anti-wear properties.
    The heel 130 generally comprises at least one wiper 230 extending radially outward from the platform 200. The wiper 230 extends between the two edges, that is to say that when the blade 100 is installed, it extends along the circumference of the vein. The wiper 230 has a sealing function. More specifically, the heel 130 may include an upstream wiper 230 and a downstream wiper 235, the upstream and downstream being defined according to the direction of flow of the fluid.
    The upstream wipers 230 and downstream 235 can be made in such a way that, when several moving blades 100 are fixed on a rotor disc, the wipers 230 and 235 of the blades are arranged edge to edge so as to form a rotary ring according to the axis of rotation of the blades, this ring being contained substantially in a radial plane, orthogonal to the main axis of the turbomachine. Such a ring makes it possible to limit the play existing between the blades and a stator, or a stator shell, which surrounds them, in order to limit any gas leaks there.
    The platform 200 has a central part 206 extending between the upstream and downstream 235 wipers 235. The central part 206 of the platform 200 then partially receives the central portion 330 of the removable part 300.
    In this embodiment of the blade, with two wipers 230, 235, the removable part extends over the central part 206, between the two wipers 230, 235. In particular, the central part 320 of the removable part 300 can marry the bowl shape generated wipers 230, 235.
    The inter-blade dimensions are different depending on the turbine stages. It is then necessary to provide removable parts with the appropriate dimensions.
    The establishment of the removable part 300 is relatively slow and inexpensive. It suffices for an operator to deform it.
    Once worn, simply replace it.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    claims
    1. Assembly comprising: - a movable blade (100) for a turbomachine comprising a heel (130), - a removable part (300) comprising an anti-wear material, configured to be removably fixed at an edge of the heel (130) to limit wear on the heel (130).
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the heel (130) comprises a platform (200) having a first edge (210) on the lower side (112) of the blade (100) and a second edge (220) on the upper side ( 114) of the blade (100), in which the removable part (300) is configured to be fixed on one of the two edges (210, 220).
    [3" id="c-fr-0003]
    3. The assembly of claim 2, wherein the removable part (300) has at least one folded end (310, 320) in the form of a hook for sandwiching a portion of the platform (200) at said edge (210, 220).
    [4" id="c-fr-0004]
    4. The assembly of claim 2 or 3 wherein the removable part (300), when fixed on the blade (100), extends from the first edge (210) to the second edge (220).
    [5" id="c-fr-0005]
    5. Assembly according to any one of claims 2 to 4, in which the removable part (300) has two ends folded in the form of a hook (310, 320) for sandwiching a portion of the first edge (210) and a portion from the second edge (220).
    [6" id="c-fr-0006]
    6. Assembly according to any one of the preceding claims, in which the heel (130) comprises two sealing wipers (230, 235) extending from the platform (200) and in which, when installed, the removable part (300) is located between the two wipers (230, 235).
    [7" id="c-fr-0007]
    7. An assembly according to any one of claims 1 to 6, wherein the removable part (300) is made of said anti-wear material.
    [8" id="c-fr-0008]
    8. An assembly according to any one of claims 1 to 6, wherein the removable part (300) comprises a coating of said anti-wear material.
    [9" id="c-fr-0009]
    9. Assembly according to any one of the preceding claims, in which the removable part (300) is deformable, in order to allow its attachment to the heel (130) of the blade (100), preferably by elastic deformation.
    [10" id="c-fr-0010]
    10. Removable part intended to be used in an assembly according to any one of the preceding claims, in which the removable part comprises characteristics defined in any one of claims 3 to 5 and 7 to 9..
    [11" id="c-fr-0011]
    11. A turbine comprising a plurality of assemblies according to any one of claims 1 to 9, in which, for two blades (100) successively arranged, the respective removable parts (300) are in contact with the anti-wear material.
    [12" id="c-fr-0012]
    12. Stellitage method using an assembly according to any one of claims 1 to 9, comprising a step of mounting the removable part (300) on the heel (130) of the blade (100) in deforming said removable part (300).
    类似技术:
    公开号 | 公开日 | 专利标题
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    FR2961554A1|2011-12-23|ANGULAR RECTIFIER SECTOR FOR TURBOMACHINE COMPRESSOR, TURBOMACHINE RECTIFIER AND TURBOMACHINE COMPRISING SUCH A SECTOR
    FR2978798A1|2013-02-08|Angular sector for rectifier of compressor in turbine of turboshaft engine e.g. turbojet, of aircraft, has hook projecting toward from suction face of blade, and recess receiving thinned part of external ring of sector of adjacent rectifier
    FR2960589A1|2011-12-02|Paddle wheel i.e. low pressure turbine wheel, for turboshaft engine e.g. turbopropeller, of airplane, has sealing units arranged between piece and upstream ends of platforms of paddles
    EP2788589B1|2015-10-14|Releasable device for axially blocking a sealing ring with which an aircraft turbomachine module rotor wheel makes contact
    FR3052822A1|2017-12-22|TURBOMACHINE DAWN EQUIPPED WITH AN ELASTOMER SEAL
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    EP3382242A1|2018-10-03|Brush seal for a turbine engine rotor
    WO2015181489A1|2015-12-03|Sealing plate with fuse function
    EP3201438B1|2021-07-28|Rotor blade of a turbomachine comprising a flange which abuts a blocking notch of a rotor disc
    FR2974142A1|2012-10-19|Immobilization device for ring used for retaining radial blade on disc of rotor of turboshaft engine, has stop including support face that is tilted relative to axial median plane of stop such that face is directed radially toward outside
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    FR3072716B1|2019-09-27|TURBOMACHINE ROTOR DARK, TURBOMACHINE ASSOCIATED
    FR3111158A1|2021-12-10|Removable anti-wear part for dawn heel
    FR3070183B1|2019-09-13|TURBINE FOR TURBOMACHINE
    FR3099520A1|2021-02-05|Turbomachine wheel
    FR3092861A1|2020-08-21|TURBOMACHINE ASSEMBLY WITH A CLAMP ON A SEALING RING
    FR3106615A1|2021-07-30|Turbomachine assembly
    同族专利:
    公开号 | 公开日
    US10895159B2|2021-01-19|
    GB2564006A|2019-01-02|
    GB201808585D0|2018-07-11|
    US20180347380A1|2018-12-06|
    GB2564006B|2022-02-16|
    FR3066780B1|2019-07-19|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1873401A2|2006-06-29|2008-01-02|Snecma|Turbomachine rotor and turbomachine comprising such a rotor|
    EP1936119A2|2006-12-14|2008-06-25|General Electric Company|Turbine blade with device preventing wear at tip shroud|
    US20120195766A1|2011-02-02|2012-08-02|Snecma|Cmc turbine engine blades and a rotor wheel for a turbine engine and a turbine engine integrating them|
    FR2985759A1|2012-01-17|2013-07-19|Snecma|MOBILE AUB OF TURBOMACHINE|FR3111158A1|2020-06-04|2021-12-10|Safran Aircraft Engines|Removable anti-wear part for dawn heel|GB1186240A|1967-12-22|1970-04-02|Rolls Royce|Improvements in Blades for Fluid Flow Machines.|
    JPH11336502A|1998-05-27|1999-12-07|Mitsubishi Heavy Ind Ltd|Steam turbine moving blade and steam turbine having the same|
    FR2938872B1|2008-11-26|2015-11-27|Snecma|ANTI-WEAR DEVICE FOR AUBES OF A TURBINE DISPENSER OF AERONAUTICAL TURBOMACHINE|
    FR2955904B1|2010-02-04|2012-07-20|Snecma|TURBOMACHINE BLOWER|
    FR3001758B1|2013-02-01|2016-07-15|Snecma|TURBOMACHINE ROTOR BLADE|
    CA2897965C|2013-03-11|2020-02-25|David J. Thomas|Compliant intermediate component of a gas turbine engine|
    JP6138575B2|2013-05-16|2017-05-31|三菱日立パワーシステムズ株式会社|Axial turbomachinery rotor blades|
    PL2808486T3|2013-05-27|2017-11-30|MTU Aero Engines AG|Balancing component for a rotor blade arrangement|
    FR3066780B1|2017-05-24|2019-07-19|Safran Aircraft Engines|ANTI-WEAR REMOVABLE PIECE FOR DAWN HEEL|FR3066780B1|2017-05-24|2019-07-19|Safran Aircraft Engines|ANTI-WEAR REMOVABLE PIECE FOR DAWN HEEL|
    US10294801B2|2017-07-25|2019-05-21|United Technologies Corporation|Rotor blade having anti-wear surface|
    法律状态:
    2018-04-23| PLFP| Fee payment|Year of fee payment: 2 |
    2018-11-30| PLSC| Publication of the preliminary search report|Effective date: 20181130 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 4 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1754601A|FR3066780B1|2017-05-24|2017-05-24|ANTI-WEAR REMOVABLE PIECE FOR DAWN HEEL|
    FR1754601|2017-05-24|FR1754601A| FR3066780B1|2017-05-24|2017-05-24|ANTI-WEAR REMOVABLE PIECE FOR DAWN HEEL|
    GB1808585.2A| GB2564006B|2017-05-24|2018-05-24|Removable anti-wear part for blade tip|
    US15/988,386| US10895159B2|2017-05-24|2018-05-24|Removable anti-wear part for blade tip|
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