• 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:
    Vibration damping device (40) for turbomachine blades (14), comprising a body (42) configured to be located between platforms (18) of two adjacent blades of a turbomachine rotor (10) and a disk ( 12) of said rotor, the device comprising at least one bearing surface (48a, 48b) configured to be applied against a lower or radially inner surface of at least one of said platforms, characterized in that it comprises at least a part fastener (44) configured to be attached to said disk.
    公开号:FR3047512A1
    申请号:FR1650921
    申请日:2016-02-05
    公开日:2017-08-11
    发明作者:Philippe Guillemin；Jacky Rodriguez
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Vibration damping device for turbomachine blades
    TECHNICAL AREA
    The present invention relates to a vibration damping device for turbomachine blades.
    STATE OF THE ART The state of the art includes documents EP-A1-1 164 253 and FR-A1-2 927 357.
    A turbomachine rotor may comprise a disk or hub at the periphery of which are provided mounting cells of blade roots. The blades each comprise a blade connected by a platform to a foot. The blade roots are fitted into the cavities of the disk so that the platforms are arranged circumferentially (with respect to the axis of rotation of the rotor) next to one another and define by their upper or radially external surfaces (for example relative to the axis of rotation of the rotor) the inner periphery of an annular flow stream of an air flow in the turbomachine. This is particularly the case of a turbomachine fan whose platforms are inclined upstream to downstream (in the direction of flow of the airflow) to the outside and thus form a frustoconical surface for guiding the flow of air. air towards the engine inlet and in particular a compressor of the turbomachine.
    It is known to associate with this type of rotor and blades vibration dampers. In the prior art as described in the aforementioned documents, a damper is formed by a metal sheet and is interposed between two adjacent blades, radially between the platforms of these blades and the disk. This damper comprises at least one bearing surface configured to be applied against lower or radially inner surfaces of the blade platforms.
    In operation, the blades are biased radially outwardly due to centrifugal forces. The dampers are also biased radially outwards against the platforms and cooperate by friction with these platforms to damp the vibrations to which the blades are subjected.
    In the current technique, the dampers are housed between the blade roots and more exactly between the stilts of these blades, connecting the feet to the platforms. However, some blades comprise at their stilts projecting elements that hinder or prevent the mounting of the dampers in this area. These projecting elements extend from the stilts in the circumferential direction to the longitudinal edges of the platform and are intended to prevent an overlap of the platforms in a particular case where the blades may bend after ingestion of a foreign body for example.
    Moreover, the mounting of dampers between blade roots has drawbacks. There is a risk of bad mounting of a damper between two blades. After mounting the blades on the disk, the dampers are no longer visible and it is not possible to verify that they are correctly positioned.
    Another problem related to the mounting of the dampers between the blade roots is due to the fact that they are not maintained axially and that they are therefore likely to move axially in operation. The frustoconical shape of the fan blade platforms accentuates this phenomenon because, under the effect of centrifugal forces, the dampers tend to slide on the radially inner surfaces of the platforms and to move axially downstream and outwards.
    The present invention provides a simple, effective and economical solution to at least some of the above problems.
    DESCRIPTION OF THE INVENTION The invention proposes a vibration damping device for turbomachine blades, comprising a body configured to be located between platforms of two adjacent blades of a turbomachine rotor and a disk of said rotor, the device comprising at least one bearing surface configured to be applied against a lower or radially inner surface of at least one of said platforms, characterized in that it comprises at least one attachment portion configured to be fixed to said disk.
    Unlike dampers of the prior art, the damping device is here fixed to the rotor disc. There is therefore no risk of involuntary axial displacement of the device in operation. In addition, the risk of poor mounting or misplacement of the device is limited or eliminated. Advantageously, the fixing of the body on the disk takes place at an axial end of the disk so as to be able to visualize this fixation even after mounting the complete annular row of blades on the disk.
    The device according to the invention may comprise one or more of the following features, taken separately from each other or in combination with each other: said body is formed by a metal sheet, preferably an elastic sheet, or of any elastic material, - Said body carries a pad of elastic material, the latter being covered with a plate, for example titanium, defining said at least one bearing surface. said body has a generally elongated shape, one longitudinal end of which comprises said fixing portion, said body is deformable in flexion in a longitudinal plane, said attachment portion comprises a passage orifice of a screw-type fixing means; nut for example, - said body comprises lateral tongues, preferably elastic, - said tabs are configured to form support means or connection, - the fixing portion is a tab. The invention also relates to a set of devices as described above, characterized in that the devices are arranged circumferentially next to each other, with respect to an axis of rotation of said rotor, so as to form an angular sector or a complete ring.
    Advantageously, said bodies are circumferentially supported on each other or are connected to each other, with respect to an axis of rotation of said rotor, through their lateral tongues. The invention also relates to a turbomachine rotor, comprising an annular array of vanes and a rotor disc having at its periphery foot mounting cells of said vanes, characterized in that it comprises an assembly as described above. , the fixing portion of each body being fixed on the disk and for example on a flange of the disk.
    Advantageously, each device is mounted prestressed radially, with respect to an axis of rotation of the rotor, between the disk and blade platforms.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIGS. 1 to 3 are diagrammatic perspective views of a partially disassembled turbomachine rotor, this rotor being equipped with one or more damping devices according to the invention, and FIGS. 4a to 4c are diagrammatic views of perspective of a device according to the invention.
    DETAILED DESCRIPTION
    FIGS. 1 to 3 show a turbomachine rotor 10 and more exactly a fan rotor of a turbomachine, the fan being situated upstream of the turbomachine with reference to the flow of gases therein.
    The rotor 10 comprises a disk 12 or hub and an annular row of blades 14, in this case fan, carried by the disk. Each blade 14 comprises a blade 16 connected by a platform 18 to a foot 20, the part of the foot connected to the platform being called stilt 22.
    In the example shown, the feet 20 of the blades 14 are of the dovetail type. Each blade 14 comprises projecting elements 24, formed in one piece with the blade, which extend respectively from the two sides of the foot 20, between the stilt 22 and the longitudinal edges 24 of the platform.
    The feet 20 are fitted into cavities 26 of complementary shape to the outer periphery of the disk 12. The cells 26 are separated from each other by teeth 28 which are each connected at their downstream end to a substantially radial flange 30 with respect to the axis of rotation of the rotor 10, which is not visible in the drawings. Each flange 30 comprises an axial orifice (parallel to the axis of rotation) for passage of a fixing means 32 of the screw-nut type.
    The feet 20 can be mounted with clearance in the cells 26 and are generally pressed against shoulders of these cells by means of spacers 34 interposed between the feet and the bottoms of the cells (Figure 2).
    In the mounting position shown in Figures 1 and 2, the platforms 18 are arranged circumferentially next to each other and around the disc 12, their longitudinal edges 24 being separated from each other by small circumferential gaps.
    The radially outer surfaces of the platforms 18 define the internal periphery of the flow passage of a flow of air passing through the fan and entering the turbomachine. These radially outer surfaces of the platforms 18 form a substantially frustoconical overall surface, flared from upstream to downstream.
    As can be seen in FIGS. 1 and 2, the root 20 of each vane 14 comprises a substantially radial downstream edge 36 having a recess 38, here in its portion joining the platform 18.
    A rotor 10 of this type is equipped with a series of vibration damping devices to which the vanes 14 are subjected during operation.
    One embodiment of the damping device 40 according to the invention is visible in the drawings and shown alone in FIGS. 4a to 4c.
    This device 40 comprises a body 42 formed here of a metal sheet folded for example by stamping. Alternatively, the body 42 is for example sheet metal. The body 42 has a generally elongate shape whose axis of elongation is intended to have a substantially radial orientation (relative to the axis of rotation of the rotor) when the device is mounted on the disk 12 (Figure 3).
    The body 42 comprises at a radially inner end a lug 44 for fixing the disk 12. This lug is intended to be applied and fixed to a flange 30 of the disk, and comprises a hole 46 for the passage of the fixing means 32 mentioned above.
    The tab 44 has a generally V-shaped or flared radially outwardly. As seen in Figure 4b, it is substantially flat and extends in a first plane P1, which may be a plane transverse to the axis of rotation of the rotor when the device is mounted on the disk.
    The body includes a radially outer end 42a and a medial portion 42b connecting the outer end to the tab 44 (inner end). The median portion 42b extends in a second plane P2 parallel to the plane P1 and offset from the latter. The outer end 42a extends in a plane P3 inclined relative to the planes P1, P2. The inclination is such that in mounting position on the disc, this end 42a extends radially downstream and outwardly. This inclination is preferably a function of that of the aforementioned frustoconical surface defined by the platforms 18 of the vanes 14.
    As illustrated in Figures 1 and 2, the device 40 is attached to a flange 30 and applied to an upstream face of this flange. Its lug 44 is interposed between the flange and the screw head or the nut of the fixing means 32 and has a stress distribution function, similar to that of a washer.
    The device 40 extends substantially radially outwards, its axis of elongation being situated in a plane passing through the axis of rotation of the rotor and by the flange 30 on which it is fixed. It is thus intended to extend between two adjacent blades 14 and more exactly between the feet 20 of these blades. The radially outer end 42a of the body 42 extends substantially parallel to the downstream ends of the platforms 18 and radially inside the latter. This end carries an elastic pad 47, for example elastomer, surmounted by a plate 48, for example titanium, intended to cooperate by support and friction with the radially inner surfaces of the platforms 18 of the adjacent blades. As seen in Figures 1 and 2, the pad 47 and the plate 48 have complementary shapes of these platform surfaces. The plate 48 defines two inclined lateral surfaces 48a, 48b intended to cooperate respectively with the platforms 18 of the adjacent blades.
    The body 42 is deformable in bending in a longitudinal plane, that is to say a plane passing through the longitudinal axis or rotation of the rotor.
    Preferably, the device 40 is mounted on the disc 12 so that the plate 48 is mounted prestressing radially against the platforms 18. This prestressing ensures that the device 40 will be sufficiently pressed against the platforms in operation to ensure their damping function, the blades being susceptible, because of their mass, to move more than the device under the effect of centrifugal forces.
    Advantageously, the device 40 comprises lateral tabs 50. These tabs 50 are intended to cooperate with tabs 50 of adjacent devices 40 (Figure 2). The tabs 50 extend in circumferential directions (relative to the axis of rotation of the rotor) from the above-mentioned middle portion 42b of the body. Each tab 50 is generally L-shaped and comprises a first portion 50a extending circumferentially from the medial portion 42b, in the same plane P2 as the latter, and a second portion 50b perpendicular to the first portion 50a and oriented here to 'downstream.
    The devices 40 of the same rotor are intended to cooperate with each other by circumferential support (relative to the axis of rotation of the rotor) of their tabs 50 and in particular second portions 50b of these tongues. This makes it possible to maintain the devices on the disk circumferentially, these devices being held axially and radially on the disk by the fixing means 32.
    As seen in Figures 1 and 2, the tabs 50 of the devices 40 are substantially housed in the recesses 38 of the blade roots.
    In the example shown, the devices 40 are mounted independently of each other on the disc 12, preferably before the blades 14 are mounted on the disc. After mounting the vanes, it is understood that the devices 40 remain visible from the downstream of the rotor 10.
    In an alternative embodiment not shown, at least some of the devices 40 could be linked to each other. It would for example be possible to weld the devices at the second portions 50b of their tabs. The devices would then be preassembled by block or angular sector which could simplify and speed up the assembly. It would also be conceivable to secure all the devices so as to have a ring or ring of devices 40 to be assembled on the disk 12. The devices 40 could also be made in one piece.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. A device (40) for vibration damping for turbomachine blades (14), comprising a body (42) configured to be located between platforms (18) of two adjacent blades of a turbomachine rotor (10) and a disk (12) of said rotor, the device comprising at least one bearing surface (48a, 48b) configured to be applied against a lower or radially inner surface of at least one of said platforms, characterized in that it comprises at least an attachment portion (44) configured to be attached to said disk.
    [2" id="c-fr-0002]
    2. Device (40) according to claim 1, wherein said body (42) is formed by a metal sheet, preferably elastic.
    [3" id="c-fr-0003]
    3. Device (40) according to claim 1 or 2, wherein said body (42) carries a pad (47) of elastic material, the latter being covered with a plate (48), for example titanium, defining said to less a support surface.
    [4" id="c-fr-0004]
    4. Device (40) according to one of the preceding claims, wherein said body (42) has a generally elongate shape, a longitudinal end comprises said fixing portion (44).
    [5" id="c-fr-0005]
    5. Device (40) according to the preceding claim, wherein said body (42) is deformable in bending in a longitudinal plane.
    [6" id="c-fr-0006]
    6. Device (40) according to one of the preceding claims, wherein said fixing portion (44) comprises a hole (46) for passage of a fastening means (32) of the screw-nut type for example.
    [7" id="c-fr-0007]
    7. Device (40) according to one of the preceding claims, wherein said body (42) comprises lateral tabs (50), preferably elastic.
    [8" id="c-fr-0008]
    8. Set of devices (40) according to one of the preceding claims, characterized in that the devices are arranged circumferentially next to each other, with respect to an axis of rotation of said rotor, so as to form an angular sector or a complete ring.
    [9" id="c-fr-0009]
    9. Assembly according to the preceding claim, each device being as defined in claim 7, wherein said body (42) is circumferentially supported on each other, with respect to an axis of rotation of said rotor, or are connected to each other. to each other via their side tabs (50).
    [10" id="c-fr-0010]
    A turbomachine rotor (10) having an annular array of vanes (14) and a rotor disk (12) having at its periphery foot mounting cells (26) (20) of said vanes, characterized in that it comprises an assembly according to claim 8 or 9, the fixing portion (44) of each body (42) being fixed on the disk and for example on a flange (30) of the disk.
    [11" id="c-fr-0011]
    11. Rotor (10) according to the preceding claim, wherein each device is mounted radially prestressed, relative to an axis of rotation of the rotor, between the disc (12) and platforms (18) of the blades (14).
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3047512B1|2019-11-15|VIBRATION DAMPING DEVICE FOR TURBOMACHINE BLADE
    CA2440995C|2011-02-08|Control of the axial position of a fan blade
    CA2769781C|2017-07-25|Vibration-damping shim for a fan blade
    EP1970537B1|2009-12-16|Turbomachine fan
    EP2344719B1|2014-01-22|Annular flange for fixing rotor or stator components in a turbomachine
    FR3027949B1|2019-07-26|TURBINE WHEEL FOR A TURBOMACHINE
    FR2972759A1|2012-09-21|Wheel for rotor of low pressure turbine in e.g. turbojet of airplane, has annular part defining radial plane to axially support blades and align blades with disk, and tightly maintained against downstream faces of teeth by downstream plate
    CA2824379C|2018-07-03|Fan rotor and associated turbojet engine
    FR2963382A1|2012-02-03|Turbine wheel for turboshaft engine e.g. turbojet of airplane, has shock absorbers covered with thin layer of hard material on platforms of blades and comprising axial sealing units limiting or preventing passage of air between stilts
    WO2011012679A2|2011-02-03|Outer shell sector for a bladed stator ring of an aircraft turbine engine, comprising vibration-damping blocks
    FR2958323A1|2011-10-07|COMPRESSOR RECTIFIER STAGE FOR A TURBOMACHINE.
    FR2986836A1|2013-08-16|ANTI-WEAR ANNULAR TOOL FOR A TURBOMACHINE
    FR3029960A1|2016-06-17|AUBES WHEEL WITH RADIAL SEAL FOR A TURBOMACHINE TURBINE
    FR2927357A1|2009-08-14|Vibration damping device for blades of high pressure rotor in high pressure turbine of e.g. aeronautical jet engine, has rib partially inserted in groove formed by edges, where rib has variable transversal section in direction of its length
    FR2971022A1|2012-08-03|COMPRESSOR RECTIFIER STAGE FOR A TURBOMACHINE
    FR3006364A1|2014-12-05|TURBOMACHINE WHEEL, IN PARTICULAR FOR LOW PRESSURE TURBINE
    FR3027950B1|2019-10-18|TURBINE WHEEL FOR A TURBOMACHINE
    EP1818507A1|2007-08-15|Rotor wheel of a turbomachine
    FR2965291A1|2012-03-30|Unitary assembly for disks of rotor of low pressure turbine of turboshaft engine e.g. turbojet engine, of airplane, has collar comprising downstream part that is formed with air passage openings opened in annular space
    FR3029961A1|2016-06-17|AUBES WHEEL WITH BECQUETS FOR A TURBOMACHINE TURBINE
    FR3039854B1|2019-08-16|INTERMEDIATE CASE FOR TURBOMACHINE HAVING IMPROVED FASTENING MEANS
    WO2014037653A1|2014-03-13|Fan rotor, in particular for a turbo engine
    FR3075255A1|2019-06-21|TURBINE DAWN
    FR3069572B1|2019-08-16|ROTOR DARK FOR AN AIRCRAFT TURBOMACHINE
    FR3074839B1|2019-11-08|TURBOMACHINE ROTOR MULTIPAL ROTOR AUB AND ROTOR COMPRISING SAME
    同族专利:
    公开号 | 公开日
    FR3047512B1|2019-11-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5205713A|1991-04-29|1993-04-27|General Electric Company|Fan blade damper|
    US5820346A|1996-12-17|1998-10-13|General Electric Company|Blade damper for a turbine engine|
    EP1985810A1|2007-04-27|2008-10-29|Snecma|Turbomachine vane damper|
    WO2011018425A1|2009-08-11|2011-02-17|Snecma|Vibration-damping shim for a fan blade|
    FR2963382A1|2010-08-02|2012-02-03|Snecma|Turbine wheel for turboshaft engine e.g. turbojet of airplane, has shock absorbers covered with thin layer of hard material on platforms of blades and comprising axial sealing units limiting or preventing passage of air between stilts|
    US20130064668A1|2011-09-08|2013-03-14|II Anthony Reid Paige|Turbine rotor blade assembly and method of assembling same|FR3075284A1|2017-12-18|2019-06-21|Safran Aircraft Engines|SHOCK ABSORBER DEVICE|
    FR3075283A1|2017-12-15|2019-06-21|Safran Aircraft Engines|SHOCK ABSORBER DEVICE|
    WO2020239803A1|2019-05-29|2020-12-03|Safran Aircraft Engines|Assembly for turbomachine|
    FR3096730A1|2019-05-29|2020-12-04|Safran Aircraft Engines|Turbomachine assembly|
    FR3096729A1|2019-05-29|2020-12-04|Safran Aircraft Engines|Turbomachine assembly|
    US10927683B2|2017-12-14|2021-02-23|Safran Aircraft Engines|Damping device|
    法律状态:
    2017-02-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-08-11| PLSC| Publication of the preliminary search report|Effective date: 20170811 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-01-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 6 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1650921|2016-02-05|
    FR1650921A|FR3047512B1|2016-02-05|2016-02-05|VIBRATION DAMPING DEVICE FOR TURBOMACHINE BLADE|FR1650921A| FR3047512B1|2016-02-05|2016-02-05|VIBRATION DAMPING DEVICE FOR TURBOMACHINE BLADE|
    [返回顶部]