• 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:
    A turbomachine turbine (10) movable ring assembly (4) which is mounted between two successive rotor disks (20a) and (20b) of said turbine (10), said rotor disks (20a) and (20b) being fastened to one another by bolting, characterized in that it comprises: - a ferrule (44) fixed between the upstream discs (20a) and downstream (20b), by bolting them, - a piece forming a mobile ring (42), said piece carrying radial sealing lips (32) and being fixed between the upstream disc (20a) and the ferrule (44), - a seal (46) interposed between said movable ring piece (42) and ferrule (44).
    公开号:FR3057300A1
    申请号:FR1659685
    申请日:2016-10-07
    公开日:2018-04-13
    发明作者:Vincent Francois Georges Millier；Francois Pierre Michel Comte；Fabien Stephane Garnier；Alain Dominique Gendraud；Arnaud Lasantha Genilier
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    (57) Movable ring assembly (4) of a turbomachine turbine (10) which is mounted between two successive rotor disks (20a) and (20b) of said turbine (10), said rotor disks (20a) and ( 20b) being fixed to each other by bolting, characterized in that it comprises:
    a ferrule (44) for fixing fixed between the upstream (20a) and downstream (20b) discs, by bolting them,
    a part forming a movable ring (42), said part carrying radial sealing wipers (32) and being fixed between the upstream disc (20a) and the ferrule (44),
    - A seal (46) interposed between said part forming a movable ring (42) and the ferrule (44).
    i
    FIELD OF THE INVENTION
    The invention relates to a movable ring assembly for a turbomachine turbine.
    STATE OF THE ART
    FIG. 1 represents an example of a turbine part of a turbomachine known from the state of the art.
    The turbine 10 consists of a distributor formed by a plurality of fixed vanes 12 arranged in a flow passage 14 and a movable wheel placed behind the distributor and formed by a plurality of movable vanes 16 also arranged in the flow stream 14 and mounted by their foot in cells 18 of rotor discs 20a, 20b, 20c, 20d, 20e.
    The rotor discs of the turbine 20a, 20b, 20c, 20d, 20e are centered on the longitudinal axis XX and are generally assembled together by means of upstream 22 and downstream ferrules 24 which are fixed to each other by bolted connections 26 passing through fixing flanges 221 and 241. This assembly of discs is itself connected to a turbine shaft (not shown) to be driven in rotation.
    In addition, a movable ring 28 carrying radial wipers 32 is disposed at the junction between each successive rotor disc, facing the corresponding fixed vane 12.
    It is fixed in the bolted connection 26 and comprises a downstream retaining flange 30 bearing against the socket 18.
    Certain movable rings 28 may also include an upstream flange 31 ensuring the maintenance of a retaining ring 27 bearing against the bladed disc (20a, 20b) upstream of the movable ring.
    The radial wipers 32 of each movable ring 28 cooperate with the internal annular surface of the fixed vane 12 opposite said ring 28 and thus ensure the seal between the upstream cavity and the downstream cavity of the turbine.
    However, the outer annular portion of the movable ring 28 is subjected to very high temperatures due to the hot air flow stream 14. This results in a strong thermal gradient between the outer annular portion of the rings 28 and their internal annular portion. This gradient causes high stresses at the level of the mounting flanges 221 and 241. It leads to the phenomenon known as "opening the flanges" which reduces the life of the rotor discs of a turbomachine turbine.
    This phenomenon is more particularly illustrated in FIG. 2 which constitutes an enlargement of the external annular portion of the bolted connection 26 between the fixing flanges 241 of the downstream ferrule 24 of an upstream disc, 221 of the upstream ferrule 22 of a downstream disc, and 442 of the movable ring 28 disposed between the upstream disc and the downstream disc. The vertical arrow illustrates the direction and direction of the mechanical stresses resulting from the thermal gradient in the mobile ring 28 which is deformed. This results in creep of said movable ring 28. The horizontal arrows represent the phenomenon of opening of flanges 241 and 221 which accompanies creep.
    DESCRIPTION OF THE INVENTION
    One of the aims of the invention is to increase the service life of turbomachine turbines by limiting the phenomenon of flange opening at the junction between successive rotor discs.
    Another object of the invention is to allow better mechanical strength of the junction flanges of successive rotor disks of a turbomachine turbine subjected to high thermal stresses.
    Another object of the invention is to provide cooling of the junction cells between the rotor discs and the turbine blades.
    Another object of the invention is to provide sealing between the upstream and downstream cavities of the turbine.
    Another object of the invention is to maintain retaining rings at the junction between blade and rotor disc.
    Another object of the invention is to simplify the maintenance of turbomachine turbines.
    In this regard, the subject of the invention is an assembly of a movable ring of a turbomachine turbine which is mounted between two successive rotor disks of said turbine, said rotor disks and being fixed to each other by bolting. , characterized in that it comprises:
    a fixing ferrule fixed between the upstream and downstream discs, by the bolting of these, a part forming a movable ring, said part carrying radial sealing wipers and being fixed between the upstream disc and the ferrule, a gasket sealing interposed between said piece forming a movable ring and the ferrule.
    Advantageously, but optionally, the movable ring assembly according to the invention can also comprise at least one of the following characteristics:
    the movable ring is hooped on the upstream disc, the ferrule comprises at least one lunula above the bolted connection, the ferrule comprises several lunulae distributed periodically at a portion of the tangential surface downstream of the ferrule, l the movable ring assembly comprises a set of grooves and tenons ensuring the anti-rotation of the movable ring relative to the ferrule, the grooves are arranged in the movable ring and the tenons extend from the ferrule, which the grooves of the movable ring are arranged in an anti-rotation flange extending from an internal annular surface of the movable ring, and distributed periodically over an annular zone of said flange remote from the internal annular surface of the movable ring, the pins are distributed periodically and regularly over an external annular surface of the ferrule, opposite the corresponding grooves of the annular flange ti-rotation of the movable ring, and the movable ring further comprises an upstream annular flange extending from a portion of tangential surface upstream of the movable ring and maintaining a retaining ring in abutment against the disc upstream.
    The invention also relates to a turbomachine, comprising an assembly according to the above description.
    The proposed solution for assembling a movable ring of a turbomachine turbine makes it possible to dissociate the external annular portion of movable rings from the bolted connection so that the movable ring is no longer exposed to the temperature gradient. Disc flanges are subject to greatly reduced stresses and their service life is significantly increased.
    In addition, the proposed solution allows the initial functions of the movable rings to be preserved. Indeed, the seal between the upstream cavity and the downstream cavity is ensured thanks to the wipers. In addition, ventilation of the bottom of the alveolus of the downstream disc is always permitted thanks to the lunulae formed in the internal annular portion of the ferrules. Finally, the downstream retaining flange is always in abutment against the junction between the disc and the downstream vane, and, if it is present, the upstream retaining flange maintains the retaining ring in abutment against the bladed upstream disc.
    DESCRIPTION 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:
    FIG. 1, already described, represents a part of a turbine of a turbomachine known from the state of the art,
    FIG. 2, already described also, illustrates a phenomenon of flange opening at the level of a bolted connection of rotor discs of a turbomachine turbine,
    FIG. 3 is a sectional view of an embodiment of the invention,
    FIG. 4a is a perspective view of a movable ring assembly according to the invention without the bolted connection and the downstream rotor disc appearing, and
    Figure 4b is a view in another perspective of the same assembly as Figure 4a.
    DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT OF THE INVENTION
    FIGS. 3, 4a and 4b show an assembly 4 of the mobile ring of a turbomachine turbine which comprises:
    a movable ring 42 with sealing lips 32, a ferrule 44 for fixing situated immediately downstream of the movable ring with respect to the direction of flow of the air in the turbomachine and a seal 46 interposed between the movable ring 42 and the ferrule 44.
    This assembly 4 is disposed between an upstream rotor disc 20a and a downstream rotor disc 20b and connected to these via a bolted connection 26.
    The bolted connection 26 engages a fixing flange 442 of the ferrule 44, a fixing flange 241 of a downstream ferrule 24 extending from an external annular portion of the upstream disc 20a, and a fixing flange 221 an upstream ferrule 22 extending from an outer annular portion of the downstream disc 20b. This assembly seals between the upstream cavity and the downstream cavity, allows ventilation of the downstream rotor disc 20b and maintains a retaining ring 27 in abutment against the upstream bladed disc 20a.
    We will now describe in more detail the different components of the assembly.
    Movable ring
    The movable ring 42 is a part of revolution around an axis X-X of the turbomachine. It comprises a downstream annular flange 30 bearing against a cell 18 of the bladed downstream rotor disc 20b. The external and internal annular surfaces of this flange have been referenced by 301 and 302.
    The end 303 of the flange 30, bearing against the cavity 18, may further comprise an annular groove 304 configured to receive an annular seal 305. Thus, when the movable ring 42 subjected to l 'hot air flow, the radial expansion of the end 303 along the walls of the cell 18 does not cause rupture of sealing of an air diffusion cavity 60 formed between the upstream shell 22 of the rotor disc 20b, flange 30 and ferrule 44. Thus, the annular seal 305 can be made of DMD0415 (HS25). The space 60 is particularly useful for ventilating the downstream disc 20b, as will be described more precisely below.
    Radial sealing wipers 32 extend from the external surface 301. They are configured to cooperate in operation with an internal surface 120 of an annular hub carrying the stationary vanes 12 of the distributor in order to seal between the upstream cavity and the downstream cavity located on either side of the hub carrying the fixed vanes 12.
    The movable ring 42 may further comprise an upstream annular flange 31 which extends from a flange 420 of the movable ring 42. This upstream annular flange bears against the retaining ring 27 in order to maintain it against the upstream bladed disc 20a. The retaining ring 27 has the function of axially retaining the moving blades 16.
    The movable ring 42 is hooped, at its base, on the downstream ferrule 24 of the upstream rotor disc 20a.
    The connection between the movable ring 42 and the upstream rotor disc 20a can also be used for anti-rotation of the different parts of the assembly 4 relative to each other.
    Finally, the movable ring 42 includes an annular flange known as an anti-rotation 50 extending radially inward from the internal radial annular surface 302 of the ring, and having a series of grooves 52 extending Radially inward, periodically all around the flange 50. The function of the flange 50 and the grooves 52 will be detailed later.
    Ferrule
    The ferrule 44 comprises on its upstream surface (surface 440) a circumferential groove 45 configured to receive the annular seal 46. This seal 46 is put in compression between the flange 420 of the movable ring 42 and the ferrule 44 by the bolted connection 26. Thus, in the event of loss of the connection between the movable ring 42 and the downstream ferrule 24 of the upstream rotor disc 20a, the seal 46 ensures the continuity of the seal between the upstream and downstream cavities of the turbine . In addition, since the seal 46 is located at the interface between two parts at very different temperatures, it is now up to it to be subjected to a high thermal gradient. Consequently, the seal 46 can be made of DMD0415 (HS25).
    Furthermore, the ferrule 44 also has, on the downstream side (surface 441) one or more cooling rings 43 arranged above the bolted connection 26, for example a series of circumferential rings 43 regularly distributed at a portion of downstream tangential surface 441.
    These lunules 43 allow a circulation of fresh air taken upstream of the turbine and circulating through each bolted connection 26. This fresh air circulating from upstream of the turbine is able to pass through the lunule 43 to the cavity of air diffusion 60 before diffusing into each cell 18 of the disc 20b to ventilate them.
    The fixing ferrule 44 ends, below said lunula 43 by a fixing flange 442 which is configured to allow the fixing of the ferrule 44 in the bolted connection 26. For this, the flange 442 has a series of openings distributed periodically and intended to come opposite a series of similar openings made respectively in the flanges 241 and 221 of the downstream ferrules 24 of the upstream disc 20a and upstream 22 of the downstream disc 20b.
    Anti rotation
    At its opposite end, the ferrule 44 may comprise a series of anti-rotation studs 54 which project in relation to the rest of said ferrule 44. These studs are periodically spaced around the ferrule 44 so as to be opposite grooves 52 that has the flange 50 of the movable ring 42 (Figures 4a and 4b).
    The grooves 52 and tenons 54 are configured to cooperate with each other all around the ring 42 and the ferrule 44 respectively. They therefore have substantially complementary forms.
    The movable ring 42 being dissociated from the bolted connection 26, these grooves 52 and tenons 54 ensure the locking in rotation of the different parts and the mechanical cohesion of the assembly 4.
    In addition to the rotation stop, the tenon-groove system described above can ensure the centering of the ring 42 in the assembly 4 in the event of loss of the hooping of the ring 42.
    Alternatively or in addition, the rotation stop can be enabled by a system of tenon-grooves made at the interface between the movable ring 42 and the downstream ferrule 24 of the upstream disc 20a. In this embodiment, the annular flange 50 is hooped on the external annular portion of the ferrule 44.
    Mechanical resistance and increased service life
    The proposed assembly therefore allows an increase in the life of a turbomachine turbine by reducing the phenomenon of flange opening at the bolted connections which connect the various turbine rotor discs.
    Indeed, during the flow of hot air in the turbine 10, the movable ring will heat up. Insofar as there is no longer any mechanical continuity between the movable ring 42 and the bolted connection 26, only the movable ring 42 will expand. Consequently, the external annular part of the fixing ring 44 will no longer "pull" on the flange 442 and will therefore not cause significant stresses on the other flanges 221 and 241 of the bolted connection 26.
    Consequently, the mechanical strength of the bolted connections 26 of the turbines 10 of turbomachines comprising an assembly of the type of assembly 4 which has just been described is improved. This results in an increase in their lifespan.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Movable ring assembly (4) of a turbine engine (10) which is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b ) being fixed to each other by bolting, characterized in that it comprises:
    a ferrule (44) for fixing fixed between the upstream (20a) and downstream (20b) discs, by bolting them,
    a part forming a movable ring (42), said part carrying radial sealing wipers (32) and being fixed between the upstream disc (20a) and the ferrule (44),
    - a seal (46) interposed between said part forming a movable ring (42) and the ferrule (44).
    [2" id="c-fr-0002]
    2. movable ring assembly (4) according to claim 1 wherein the movable ring (42) is hooped on the upstream disc (20a).
    [3" id="c-fr-0003]
    3. Movable ring assembly (4) according to one of the preceding claims wherein the ferrule (44) comprises at least one lunula (43) above the bolted connection (26).
    [4" id="c-fr-0004]
    4. Movable ring assembly (4) according to claim 3, wherein the ferrule comprises several lunules distributed regularly at a portion of downstream tangential surface (441) of the ferrule (44).
    [5" id="c-fr-0005]
    5. Movable ring assembly (4) according to one of the preceding claims comprising a set of grooves (52) and pins (54) ensuring the anti-rotation of the movable ring (42) relative to the ferrule (44 ).
    [6" id="c-fr-0006]
    6. Movable ring assembly (4) according to claim 5 wherein the grooves (52) are arranged in the movable ring (42) and the pins (54) extend from the ferrule (44).
    ίο
    [7" id="c-fr-0007]
    7. Movable ring assembly (4) according to claim 6 wherein the grooves (52) of the movable ring (42) are disposed in an anti-rotation flange (50) extending from an annular surface internal of the movable ring (42), and distributed periodically over an annular zone of
    5 said flange (50) remote from the internal annular surface of the movable ring (42).
    [8" id="c-fr-0008]
    8. movable ring assembly (4) according to claim 6 wherein the pins (54) are distributed periodically and regularly over a surface
    10 outer annular ring (44), opposite the corresponding grooves of the anti-rotation flange (50) of the movable ring (42).
    [9" id="c-fr-0009]
    9. movable ring assembly (4) according to one of the preceding claims wherein the movable ring (42) further comprises an annular flange
    15 upstream (31) extending from a portion of upstream tangential surface (420) of the movable ring and maintaining a retaining ring (27) bearing against the upstream bladed disc (20a).
    [10" id="c-fr-0010]
    10. Turbojet engine comprising a movable ring assembly (4) according to one
    20 any of the preceding claims.
    1/5
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3523507B1|2020-06-24|Movable ring assembly for a turbine engine turbine
    EP1517005A1|2005-03-23|Gas turbine sealing joint having lamellar structure
    EP1970538B1|2010-05-19|Turbomachine rotor disc
    EP1965027B1|2012-01-25|High-pressure turbine of a turbomachine
    EP1265031B1|2007-09-12|Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials
    EP3146157B1|2019-07-31|Turbine rotor for a gas-turbine engine
    CA2925438C|2021-09-28|Rotary assembly for a turbomachine
    FR2955898A1|2011-08-05|Turbine-stage for use in e.g. turboprop engine in airplane, has groove including sidewalls with annular rib in which annular seal is housed, where seal is clamped between bottom of groove and upstream edge of ring
    EP1519009A1|2005-03-30|Turbomachine with cabin bleed air through a tube with ball joint
    FR2954797A1|2011-07-01|Low pressure turbine rotor for two-shaft gas turbine engine of aircraft, has elastic sealing unit fixed on each of blade roots and projected with respect to rear transverse face of disk at level of joints so as to be in contact with flange
    FR3068070B1|2019-07-19|TURBINE FOR TURBOMACHINE
    FR2978793A1|2013-02-08|Turbine rotor for e.g. turbojet engine of aircraft, has annular ring deformed or moved in order to compensate deformation/displacement of plate so as to ensure sealing of annular space irrespective of position of plate
    WO2015044579A1|2015-04-02|Rotary assembly for a turbomachine
    FR3078363A1|2019-08-30|MOBILE SEAL RING
    FR2965843A1|2012-04-13|ROTOR FOR TURBOMACHINE
    EP3746639B1|2021-12-15|Assembly for a turbine of a turbomachine comprising a mobile sealing ring
    EP3152404A1|2017-04-12|Rotor for turbine engine comprising blades with added platforms
    FR3011270A1|2015-04-03|DEVICE FOR CONNECTING A FIXED PART OF A TURBOMACHINE AND A DISTRIBUTOR FOOT OF A TURBOMACHINE TURBINE
    FR3101374A1|2021-04-02|Cooling structure of a turbine with radial cooperation between sealing ring and moving wheel disc
    FR2961556A1|2011-12-23|Turbine i.e. low pressure turbine, for e.g. turbojet engine of airplane, has axial and radial support units that are not in contact with casing to avoid heating, by conduction, of casing by sectorized ring during operation
    FR3113419A1|2022-02-18|DISTRIBUTOR OF A TURBOMACHINE TURBINE
    FR3086328A1|2020-03-27|TURBINE WITH BLADES HELD AXIALLY, FOR TURBOMACHINE
    FR3088671A1|2020-05-22|SEALING BETWEEN A MOBILE WHEEL AND A DISTRIBUTOR OF A TURBOMACHINE
    EP3874131A1|2021-09-08|Turbine shroud sector with cooled sealing strips
    CA2433549A1|2002-07-11|Gas turbine engine axial stator compressor
    同族专利:
    公开号 | 公开日
    EP3523507A1|2019-08-14|
    CN109844264A|2019-06-04|
    US20200040735A1|2020-02-06|
    WO2018065739A1|2018-04-12|
    FR3057300B1|2018-10-05|
    CN109844264B|2021-04-30|
    EP3523507B1|2020-06-24|
    US10920593B2|2021-02-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1264964A1|2001-06-07|2002-12-11|Snecma Moteurs|Arrangement for turbomachine rotor with two blade discs separated by a spacer|
    US20140356172A1|2013-05-28|2014-12-04|Snecma|Turbine wheel in a turbine engine|
    US20150308279A1|2014-04-24|2015-10-29|Snecma|Rotating assembly for a turbomachine|FR3086328A1|2018-09-20|2020-03-27|Safran Aircraft Engines|TURBINE WITH BLADES HELD AXIALLY, FOR TURBOMACHINE|
    FR3111157A1|2020-06-05|2021-12-10|Safran Aircraft Engines|Motor comprising a sealing member between two rotor elements|US5080556A|1990-09-28|1992-01-14|General Electric Company|Thermal seal for a gas turbine spacer disc|
    FR2712029B1|1993-11-03|1995-12-08|Snecma|Turbomachine provided with a means for reheating the turbine disks when running at high speed.|
    JPH09242563A|1996-03-11|1997-09-16|Hitachi Ltd|Gas turbine cooling system|
    FR2868814B1|2004-04-09|2009-12-18|Snecma Moteurs|DEVICE FOR ASSEMBLING ANNULAR FLANGES, PARTICULARLY IN A TURBOMACHINE|
    FR2928963B1|2008-03-19|2017-12-08|Snecma|TURBINE DISPENSER FOR A TURBOMACHINE.|
    FR2937371B1|2008-10-20|2010-12-10|Snecma|VENTILATION OF A HIGH-PRESSURE TURBINE IN A TURBOMACHINE|
    FR2939836B1|2008-12-12|2015-05-15|Snecma|SEAL FOR PLATFORM SEAL IN A TURBOMACHINE ROTOR|
    US8221062B2|2009-01-14|2012-07-17|General Electric Company|Device and system for reducing secondary air flow in a gas turbine|
    FR2946083B1|2009-05-28|2011-06-17|Snecma|LOW PRESSURE TURBINE|
    FR2982635B1|2011-11-15|2013-11-15|Snecma|AUBES WHEEL FOR A TURBOMACHINE|EP3318723B1|2016-11-04|2021-01-13|Siemens Aktiengesellschaft|Sealing ring of a rotor and rotor|
    FR3108361A1|2020-03-19|2021-09-24|Safran Aircraft Engines|TURBINE WHEEL FOR AN AIRCRAFT TURBOMACHINE|
    FR3108938B1|2020-04-02|2022-03-04|Safran Aircraft Engines|Sealing ring for a turbomachine turbine rotor|
    法律状态:
    2017-09-20| PLFP| Fee payment|Year of fee payment: 2 |
    2018-04-13| PLSC| Search report ready|Effective date: 20180413 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 3 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1659685A|FR3057300B1|2016-10-07|2016-10-07|MOBILE RING ASSEMBLY OF TURBOMACHINE TURBINE|
    FR1659685|2016-10-07|FR1659685A| FR3057300B1|2016-10-07|2016-10-07|MOBILE RING ASSEMBLY OF TURBOMACHINE TURBINE|
    PCT/FR2017/052746| WO2018065739A1|2016-10-07|2017-10-06|Movable ring assembly for a turbine engine turbine|
    CN201780062161.5A| CN109844264B|2016-10-07|2017-10-06|Active ring assembly for turbine of turbine engine|
    EP17786988.0A| EP3523507B1|2016-10-07|2017-10-06|Movable ring assembly for a turbine engine turbine|
    US16/339,801| US10920593B2|2016-10-07|2017-10-06|Movable ring assembly for a turbine engine turbine|
    [返回顶部]