• 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 a turbomachine stage, in particular a low-pressure turbine (1), comprising a rotor (2) comprising a disc (3) carrying moving vanes (4), and a stator comprising vanes whose periphery external connector is connected to an outer casing and whose inner periphery comprises an inner ferrule (12) carrying at least one block of abradable material (12a), the rotor (2) comprising at least one sealing ferrule (15) comprising at least a wiper (15a) adapted to cooperate with the block of abradable material (12a), characterized in that the inner shell (12) comprises at least one obstacle member (32, 33) extending towards the shell of sealing (15).
    公开号:FR3039589A1
    申请号:FR1557205
    申请日:2015-07-28
    公开日:2017-02-03
    发明作者:Fabien Stephane Garnier；Cyril Bernard Loiseau；Philippe Christian Pellier
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Turbomachine stage, in particular of low pressure turbine
    The present invention relates to a turbomachine stage, in particular a low-pressure turbine.
    The patent application FR 3,006,365 in the name of the Applicant discloses a low-pressure turbine comprising a rotor and a stator forming several turbine stages, in particular four stages.
    Thus, the rotor of the low-pressure turbine comprises four wheels assembled axially to each other by annular flanges and each having a disc bearing individual blades. These vanes each comprise a blade connected by a platform to a median wall or stagger extending radially and extended radially inward by a foot which is engaged in a groove of the disk.
    The housing grooves of the blade roots define between them teeth which are surrounded by the platforms of the blades. The rotor is connected to a turbine shaft via a drive cone.
    Between the rotor wheels are annular rows of stationary blades belonging to the stator and which are mounted by appropriate means at their radially outer ends on an outer casing of the low-pressure turbine. The blades of each row are joined together at their radially inner ends by annular sectors placed circumferentially end to end so as to form an inner ring and carrying blocks of abradable material.
    Spoilers or upstream and downstream circumferential flanges are formed in axial projection on the annular sectors, and form baffles with other spoilers or circumferential edges upstream and downstream of the platforms of the blades, to limit the passage of the combustion gases, from the combustion chamber upstream of the turbine, radially from the outside to the inside.
    The blades of the rotor are retained axially on the disk by means of an annular rod which is mounted upstream of the disk and is applied axially on upstream faces of the blade roots and teeth of the disk by an annular ring of sealing that is integral with the disc.
    The ferrule, of generally frustoconical shape, extends around a frustoconical upstream flange of the disc and defines therewith an annular space of ventilation air circulation of the teeth of the disc. This air is intended to penetrate longitudinal passages extending between the blade roots and the bottoms of the grooves of the disk. The shell comprises wipers, cooperating with the blocks of abradable material to form a labyrinth type joint. The upstream end of the sealing ferrule comprises a radial flange which is fixed to a radial flange of the upstream flange of the disc by means of bolts.
    In operation, the sealing ferrule may be subjected to mechanical stresses under the effect of centrifugal forces. Simulations have shown that, if the sealing shell were to be subjected to extreme stresses, fragments of the ferrule could be caused to detach from the disk, each fragment extending circumferentially over a large angular range, from order of 120 ° for example. These fragments would then be ejected radially outwards and, because of their large mass, could pierce the outer casing of the turbine, thus severely damaging the turbomachine. The invention aims in particular to provide a simple, effective and economical solution to this problem. For this purpose, it proposes a turbomachine stage, in particular a low-pressure turbine stage, comprising a rotor comprising a disc carrying moving blades, and a stator comprising fixed vanes whose outer periphery is connected to an external casing and whose internal periphery comprises an inner ferrule carrying at least one block of abradable material, the rotor comprising at least one sealing ferrule comprising at least one wiper adapted to cooperate with the block of abradable material, characterized in that the inner ferrule comprises at least an obstacle member extending towards the sealing ferrule.
    The presence of the obstacle member makes it possible either to limit the deformation of the sealing ferrule, by supporting the latter against the said obstacle in operation, or to break any parts detaching from the sealing ferrule so as to forming portions of smaller dimensions and smaller mass, such parts then no longer having sufficient mass to pierce the outer casing. This limits the damage potential of the turbomachine.
    Each obstacle member thus has a portion located near the sealing ferrule, preferably at a distance of less than 10 mm. Of course, this distance may vary depending on the applications.
    The inner ferrule may comprise a support, the block of abradable material being fixed on the support, the obstacle member being attached to the support.
    In this case, the obstacle member may be made of material with the support of the inner shell, thus ensuring good mechanical strength of the assembly. The obstacle member may extend radially inwards and / or axially upstream or downstream.
    In addition, the rotor disc may comprise at least one annular flange extending axially upstream or downstream, the sealing ferrule being fixed to said flange and surrounding said flange.
    The sealing ferrule may comprise a locally projecting portion which extends towards the obstacle member, so as to further bring the obstacle member and the projecting portion of the sealing ferrule.
    According to one embodiment, each obstacle member may extend circumferentially over an angular range of less than 10 °, preferably of the order of 5 °.
    In addition, the stator may comprise several obstacles forming members, regularly distributed over the circumference of the rotor.
    The inner ferrule may comprise at least one obstacle member extending axially upstream and at least one obstacle member extending axially downstream. The invention will be better understood and other details, features and advantages of the invention will appear on reading the following description given by way of non-limiting example with reference to the accompanying drawings in which: - Figure 1 is a half partial diagrammatic view in axial section of a turbomachine low-pressure turbine, FIG. 2 is a partial schematic half-view in axial section and on a larger scale of a portion of the turbine of FIG. turbine wheel of the prior art, - Figure 3 is a partial schematic half-view in axial section of a portion of a low-pressure turbine of a turbomachine, illustrating a first embodiment of the invention, FIG. 4 is a view corresponding to FIG. 3, illustrating a second embodiment of the invention; FIG. 5 is a perspective view of a sector of the stator, illustrating the second embodiment of FIG. 6 is a view corresponding to FIG. 3, illustrating a third embodiment of the invention.
    In what follows, the terms "upstream" and "downstream" are defined with respect to the flow direction of the gases in the turbomachine, in particular in the secondary vein. Similarly, the terms "radial" and "axial" are defined with respect to the axis of the turbomachine.
    Referring first to Figure 1 which is a schematic half-sectional view of a low-pressure turbomachine turbine 1, in a plane passing through the axis of rotation of the rotor of the turbine 1.
    The rotor of the low-pressure turbine comprises four wheels 2 assembled axially to each other by annular flanges and each having a disc 3 carrying individual blades 4. As can be seen more clearly in FIG. 2, these vanes 4 each comprise a blade 5 connected by a platform 6 to a median or stepped wall 7 extending radially and extended radially inside by a foot 8 which is engaged. in a groove of the disc 3.
    The housing grooves of the feet 8 of the blades 4 define between them teeth which are surrounded by the platforms 6 of the blades 4. The rotor is connected to the turbine shaft via a drive cone 10 .
    Between the wheels 2 are annular rows of fixed blades 11 which are mounted by appropriate means at their radially outer ends on an outer casing 11a of the low-pressure turbine. The fixed vanes 11 of each row are joined together at their radially inner ends by annular inner ring 12 sectors circumferentially end-to-end and carrying blocks of abradable material 12a.
    Upstream and downstream circumferential spoilers or flanges 13a, 13b are formed in axial projection on the annular sectors 12, and form baffles with other upstream and downstream circumferential spoilers or flanges 6a, 6b of the platforms 6 of the blades 4, for limit the passage of combustion gases from the combustion chamber upstream of the turbine 1, radially from the outside to the inside.
    The blades 4 are retained axially on the disk 3 by means of an annular rod 14 which is mounted upstream of the disk 3 and is applied axially on the upstream faces of the blade roots 8 and the teeth of the disk 3 by a annular ferrule 15 integral with the disc 3.
    The ferrule 15 extends around an upstream flange 16 of the disk 3 and defines therewith an annular air circulation space for ventilating the teeth of the disk (arrow 17). This air is intended to penetrate longitudinal passages extending between the blade roots 8 and the bottoms of the grooves of the disk 3. The shell 15 comprises wipers 15a, cooperating with the blocks of abradable material 12a so as to form a labyrinth type joint.
    It is known to mount sealing members 18 called "candies" between the blades 4, in lateral cavities 19 facing the platforms 6 of the blades 4. Each sealing member 18 is mounted between two adjacent blades 4 and comprises a circumferential end portion housed in the side cavity 19 of a blade 4 and an opposite circumferential end portion housed in the side cavity 19 of an adjacent blade 4. These sealing members 18 follow, with slight play, the internal shape of the cavities 19.
    In operation, these sealing members 18 are subjected to centrifugal forces and are radially plated on the internal faces of the main walls 6c of the platforms 6, thus preventing the radial passage of hot gases from the vein at the support zones. . The alternation of the different wheels 2 of the rotor and the annular rows of fixed vanes 11 define several successive stages of the low-pressure turbine 1.
    As previously indicated, in operation, the sealing ring 15 may be subjected to mechanical stresses under the effect of centrifugal forces. Simulations have demonstrated that, if the sealing ring 15 were to be subjected to extreme stresses, fragments of the shell 15 could be caused to detach from the disk 3, each fragment extending circumferentially over a large angular range , of the order of 120 ° for example. These fragments would then be ejected radially outwards and, because of their large mass, could pierce the outer casing 11a of the turbine 1, thus severely damaging the turbomachine.
    Figure 3 shows a first embodiment of the invention. Note that the sealing ring 15 here comprises a radial rib 20, attached to an upstream flange 16 of the disk 3 located directly downstream and to a downstream flange 22 of the disk 3 located directly upstream. The sealing ferrule 15 further comprises a portion 23 extending upstream from the generally cylindrical rib 20, the upstream end of which has a radial flange 24 resting on a downstream flange 25 closing the cavities 19 in which are housed the corresponding sealing members 18. The sealing ring 15 further comprises a downstream portion 26 extending downstream from the rib 20 and generally frustoconical, are the downstream end comprises a radial flange 27 bearing on an upstream radial face 28 of the disk 3 to the level of which opens the grooves used for housing the feet 8 of the blades 4.
    Furthermore, the inner shell 12 has a frustoconical portion radially outer 29 delimiting a portion of the gas flow passage through the turbine 1, a radially inner cylindrical portion 30, and a portion 31 extending radially between the aforementioned parts 29, 30. The inner portion 30 supports the abradable blocks 12a.
    The radial portion 31 carries the upstream and downstream circumferential spoilers or flanges 13a, 13b. The shape of said spoilers or flanges 13a, 13b may vary depending on the applications and the stage considered within the turbine 1. In addition, it is possible that the inner ring 12 is devoid of such spoilers or flanges 13a, 13.
    Said spoilers or flanges 13a, 13 constitute baffles with the spoilers or upstream and downstream circumferential flanges 6a, 6b of the platforms 6 of the blades 4, to limit the passage of the combustion gases radially from the outside to the inside.
    In this embodiment, at least one obstacle member 32 extends radially inward and axially downstream from the downstream end of the portion 30 of the inner ferrule 12. In addition, at least one member 33 forming an obstacle extends radially inwards and axially upstream from the upstream end of the portion 30 of the ferrule 12.
    The members 32, 33 are for example circumferentially located. In this case, they may take the form of studs or fingers extending circumferentially over an angular range of between 5 and 10 ° for example of the order of 5 °. In this case also, it is possible to provide several members 32, 33, distributed for example regularly over the entire circumference.
    It is also possible to provide only members 32, 33 upstream or downstream of the inner ferrule 12, preferably only downstream of the inner ferrule 12.
    The shortest distance d between the free end, that is to say the radially inner end, of the downstream members 32 relative to the sealing ring 15 is for example between 5 and 10 mm.
    The members 32, 33 may be integral with the inner ferrule 12 or be formed of different parts, fixed to said inner ferrule 12, for example by welding.
    The corresponding annular row of blades 11 may be sectored, so that the inner ring 12 belonging to said row may also be sectored. In this case, the different sectors 34 are arranged circumferentially end to end over the entire periphery. Such a sector 34 is for example illustrated in Figure 5, this figure relating to another embodiment which will be detailed later.
    In operation, the presence of the obstacle members 32, 33 makes it possible to limit the deformation of the sealing ring 15, by supporting the latter on said member 32, 33 during operation, and possibly to break said sealing ring 15 by so as to form parts of smaller dimensions and smaller mass, such parts then no longer having a sufficient mass to pierce the outer casing 11a. This limits the damage potential of the turbomachine. It is recalled that, in the absence of the members 32, 33, the sealing ring 15 would deform until reaching its critical deformation where it would break into several large parts, generally three parts each extending over 120 ° approx.
    Figures 4 and 5 show a second embodiment, which differs from that described with reference to Figure 3 in that the inner portion 30 of the inner shell 12 has a spoiler or a flange 35 extending radially outwardly from its downstream end and at least one obstacle member 32 extending from its upstream end. This member 32 comprises a portion 36 extending axially upstream, extended by a portion 37 extending radially inwards.
    The inner ferrule 12 may comprise several localized members 32, regularly distributed on the periphery. It is for example possible to provide a member 32 per sector 34, as shown in Figure 5, the number of sectors 34 per turbine stage being for example equal to eight.
    FIG. 6 represents a third embodiment of the invention, which differs from that described above with reference to FIG. 5 in that the sealing ferrule 15, in particular the frustoconical part 26 of said ferrule 15, comprises at least a zone 38 projecting radially outwardly and located generally facing the free end of the upstream member (s) 32. Said projecting zone 38 may extend circumferentially over the entire periphery or be located circumferentially, for example in a angular range less than 20 ° preferably of the order of 5 °. In the latter case, the sealing ring 15 may comprise a plurality of projecting zones 38 situated opposite the corresponding members 32.
    In this embodiment, it is therefore possible to further reduce the distance between the free end of the member 32 and the ferrule 15, in particular between the free end of the member 32 and the corresponding projecting zone 38 of the ferrule 15.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Turbomachine stage, in particular a low-pressure turbine (1), comprising a rotor (2) comprising a disc (3) carrying moving blades (4), and a stator comprising stationary vanes (10) whose periphery external is connected to an outer casing (11a) and whose inner periphery comprises an inner ferrule (12) carrying at least one block of abradable material (12a), the rotor (2) comprising at least one sealing ferrule (15) comprising at least one wiper (15a) adapted to cooperate with the block of abradable material (12a), characterized in that the inner ring (12) comprises at least one obstacle member (32, 33) extending in the direction of the sealing ferrule (15).
    [2" id="c-fr-0002]
    2. Floor according to claim 1, characterized in that the inner shell (12) comprises a support (30), the block of abradable material (12a) being fixed on the support (30), the obstacle member (32, 33) being attached to the support (30).
    [3" id="c-fr-0003]
    3. Floor according to claim 2, characterized in that the obstacle member (32, 33) is made of material with the support (30) of the inner shell (12).
    [4" id="c-fr-0004]
    4. Floor according to one of claims 1 to 3, characterized in that the obstacle member (32, 33) extends radially inwardly and / or axially upstream or downstream.
    [5" id="c-fr-0005]
    5. Floor according to one of claims 1 to 4, characterized in that the disk (3) of the rotor (2) comprises at least one annular flange (16, 22) extending axially upstream or towards the downstream, the sealing ferrule (15) being attached to said flange (16, 22) and surrounding said flange (16, 22).
    [6" id="c-fr-0006]
    6. Floor according to one of claims 1 to 5, characterized in that the sealing ring (15) has a locally projecting portion (38) which extends towards the obstacle member (32).
    [7" id="c-fr-0007]
    7. Floor according to one of claims 1 to 6, characterized in that each obstacle member (32, 33) extends circumferentially over an angular range of less than 10 °, preferably of the order of 5 °.
    [8" id="c-fr-0008]
    8. Stage according to one of claims 1 to 7, characterized in that the stator comprises a plurality of obstacle members (32, 33) regularly distributed over the circumference of the rotor.
    [9" id="c-fr-0009]
    9. Floor according to one of claims 1 to 8, characterized in that the inner shell (12) comprises at least one obstacle member (33) extending axially upstream and at least one obstacle member (32). ) extending axially downstream.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3039589B1|2020-01-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5215435A|1991-10-28|1993-06-01|General Electric Company|Angled cooling air bypass slots in honeycomb seals|
    EP1293645A1|2001-09-14|2003-03-19|Techspace Aero S.A.|Turbomachine axial compressor with flow splitting device and assembly method for this device|
    EP2722486A1|2012-10-17|2014-04-23|MTU Aero Engines GmbH|Seal holder for a stator assembly|
    EP2801702A1|2013-05-10|2014-11-12|Techspace Aero S.A.|Inner shroud of turbomachine with abradable seal|
    FR3011031A1|2013-09-25|2015-03-27|Herakles|ROTARY ASSEMBLY FOR TURBOMACHINE|
    FR3013096A1|2013-11-14|2015-05-15|Snecma|SEALING SYSTEM WITH TWO ROWS OF COMPLEMENTARY LECHETTES|CN108979738A|2017-06-02|2018-12-11|赛峰航空助推器股份有限公司|The sealing system of turbomachine compressor|
    FR3075869A1|2017-12-21|2019-06-28|Safran Aircraft Engines|MOBILE TURBINE WHEEL FOR AIRCRAFT TURBOMACHINE, COMPRISING A SEAL RING RADIALLY RETAINED BY INCREASES ON THE ECHASSE DES AUBES|
    FR3082233A1|2018-06-12|2019-12-13|Safran Aircraft Engines|TURBINE SET|
    FR3103012A1|2019-11-12|2021-05-14|Safran Aircraft Engines|Sectorized annular row of fixed vanes|
    FR3108361A1|2020-03-19|2021-09-24|Safran Aircraft Engines|TURBINE WHEEL FOR AN AIRCRAFT TURBOMACHINE|
    法律状态:
    2016-07-20| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-03| PLSC| Search report ready|Effective date: 20170203 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 5 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 6 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1557205|2015-07-28|
    FR1557205A|FR3039589B1|2015-07-28|2015-07-28|TURBOMACHINE STAGE, PARTICULARLY LOW-PRESSURE TURBINE|FR1557205A| FR3039589B1|2015-07-28|2015-07-28|TURBOMACHINE STAGE, PARTICULARLY LOW-PRESSURE TURBINE|
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