• 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 turbine (1) for a turbomachine, in particular for an airplane turbojet or turboprop engine, comprising a housing (2) and a rotor comprising blades (29) whose radially outer periphery comprises at least one first wiper ( 31) extending radially outwardly, sealing means extending radially around the blades (29) and having a ring (14) of abradable material, the radially outer ends of the first wipers (31) being engaged in a groove (17) of said ring (14) of abradable material so as to form a labyrinth type seal, characterized in that said ring (14) is formed of a plurality of contiguous angular sectors (15), each ring sector (15) ) comprising at least one fastening member (21, 25) cooperating with at least one complementary fastening flange (4, 5) of the casing (2) so as to mount each sector (15) on the casing (2). ) by displacement axia l of said sector (15) relative to the housing (2).
    公开号:FR3058756A1
    申请号:FR1661045
    申请日:2016-11-15
    公开日:2018-05-18
    发明作者:Vincent Desforges Jean-Baptiste；Frederic Claude Cyrille Evain Gael
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Holder (s): SAFRAN AIRCRAFT ENGINES Simplified joint-stock company.
    Extension request (s)
    Agent (s): ERNEST GUTMANN - YVES PLASSERAUD SAS.
    (U4) TURBINE FOR TURBOMACHINE.
    FR 3 058 756 - A1 _ The invention relates to a turbine (1) for a turbomachine, in particular for an aircraft turbojet or turboprop, comprising a casing (2) and a rotor comprising vanes (29) whose radially outer periphery comprises at least a first wiper (31) extending radially outward, sealing means extending radially around the blades (29) and comprising a ring (14) of abradable material, the radially external ends of the first wipers (31) being engaged in a groove (17) of said ring (14) of abradable material so as to form a joint of labyrinth type, characterized in that said ring (14) is formed from several contiguous angular sectors (15), each ring sector (15) comprising at least one fixing member (21,25) cooperating with at least one complementary hooking flange (4, 5) of the casing (2) so as to assemble each sector ( 15) on the housing (2) pa r axial displacement of said sector (15) relative to the casing (2).
    Turbine for turbomachine
    The present invention relates to a turbine for a turbomachine, in particular for an aircraft turbojet or turboprop, as well as to a method for mounting such a turbine.
    A turbomachine, in particular a double body turbomachine, conventionally comprises, from upstream to downstream, a blower, a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine.
    By convention, in the present application, the terms upstream and downstream are defined with respect to the direction of air circulation in the turbomachine. Likewise, by convention in the present application, the terms internal and external, lower and upper and internal and external are defined radially with respect to the axis of the turbomachine.
    A low pressure turbine engine turbine comprises a turbine shaft on which are mounted several successive stages each comprising an impeller and a distributor. Each impeller comprises a disc carrying at its outer periphery substantially radial vanes, the discs of the different wheels being connected coaxially to each other and to the drive shaft of the turbine rotor by suitable means. Each distributor comprises an internal annular platform and an external annular platform between which extend substantially radial blades. The external platform of the distributor comprises means for hooking and fixing to an external casing of the turbine. The set of distributors forms the fixed part of the motor called the stator.
    The blades of each rotor wheel conventionally have wipers at their radially outer periphery, cooperating with a ring of abradable material so as to form sealing means of the labyrinth seal type.
    Such a structure is for example known from document FR 2 879 649.
    In order to guarantee a high efficiency of the turbomachine, it is necessary to control the clearances at the level of said seals and limit the leakage rates at the interface between the wipers of the blades and the ring of abradable material.
    There is a need to further improve the efficiency of such labyrinth seals as well as the assembly of the turbine.
    The object of the invention is in particular to provide a simple, effective and economical solution to this problem.
    To this end, the invention provides a turbine for a turbomachine, in particular for an aircraft turbojet or turboprop, comprising a casing and a rotor comprising vanes whose radially external periphery comprises at least one first wiper extending radially towards the exterior, sealing means extending radially around the blades and comprising a ring of abradable material, the radially external ends of the first wipers being engaged in a groove of said ring of abradable material so as to form a labyrinth type seal, characterized in that said ring is formed from several contiguous angular sectors, each ring sector comprising at least one fixing member cooperating with at least one additional attachment flange of the casing so as to mount each sector on the casing by axial displacement of said sector relative to the casing.
    In this way, the different sectors can be mounted around the blades so as to form the ring of abradable material, before axially engaging the assembly comprising in particular the blades and said sectors in the casing, so that the members sector fixing cooperate with the flanges to ensure the fixing of said sectors in the housing, around the blades.
    In this case, it is possible to have a first wiper which forms a labyrinth type seal with the walls of the groove, said seal having a significant pressure drop, substantially greater than in the case of the prior art. Indeed, it is possible to have a first wiper which is of large radial dimension, engaged in a groove of large radial dimension also, the mounting then being made possible by the sectorized structure of the ring and by the axial engagement of said sectors and blades in the turbine housing.
    Each flange may have a first part extending radially from a cylindrical or frustoconical wall of the casing, and a second part extending axially, cooperating with the fixing member of the corresponding ring sector.
    Each fastening member may comprise a general U-shaped section comprising branches extending axially and spaced apart radially from one another, engaging on either side of an axial part of the complementary fastening flange .
    The turbine may comprise at least a first fixing member and at least a second fixing member, axially offset from one another, capable of cooperating respectively with a first flange and a second flange of the casing.
    Each ring sector may include a block of abradable material fixed to a support, each fixing member being formed by said support or fixed to said support.
    Each blade may include at least a first wiper extending radially and at least a second wiper extending radially outward relative to the first wiper, the first wiper and the second wiper being axially offset one with respect to the other.
    The first wiper can be engaged in a first groove in the corresponding ring sector, the second wiper being engaged in a second groove in the ring sector.
    The first wiper can be engaged in a first groove in the corresponding ring sector, the radially outer end of the second wiper being located near a cylinder portion surface of the ring sector.
    The turbine may comprise a distributor, comprising a radially external platform, bearing on a flange of the casing, the sector comprising a fixing member coming to fix the external platform of the distributor on the corresponding flange of the casing, while ensuring the fixing of the sector on said flange.
    The invention also relates to a method for mounting a turbine of the aforementioned type, characterized in that it comprises the steps consisting in:
    - mount the sectors around the blades so as to form the ring of abradable material,
    - Axially engaging the assembly comprising in particular the blades and said sectors in the casing, so that the securing members of the sectors cooperate with the flanges so as to ensure the fixing of said sectors in the casing, around the blades.
    Such a method is simple and quick to implement and allows easy assembly or disassembly of the turbine.
    The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of nonlimiting example with reference to the appended drawings in which:
    FIG. 1 is a view in axial section of a part of a turbine according to an embodiment of the invention,
    FIG. 2 is an exploded perspective view of part of the turbine,
    FIGS. 3 to 5 illustrate different stages of mounting the turbine of FIGS. 1 and 2,
    - Figure 6 illustrates a blade and an abradable sector of a turbine according to an alternative embodiment of the invention.
    A low-pressure turbine 1 of a turbomachine according to a first embodiment is illustrated in FIG. 1. The turbine 1 comprises a fixed casing 2, having a frustoconical wall 3 whose axis corresponds to the axis of the turbomachine and from which flanges 4, 5 extend radially inwards. The casing 2 comprises in particular an upstream flange 4 and a downstream flange 5. The terms upstream and downstream are defined by reference to the direction of flow of the gas flow within the turbine 1, that is to say from the left right in Figure 1.
    Each flange 4, 5 has a first annular part 6 extending radially inwards from the frustoconical wall 3, and a second cylindrical part 7 extending towards the downstream.
    The upstream flange 4 further comprises an annular radial flange 8 extending radially inwards from the downstream end of the second part 7.
    The stator of the turbine 1 includes in particular a distributor stage 9, called the upstream distributor. The distributor 9 comprising a radially internal platform (not visible), a radially external platform 10 and fixed blades 11 connecting said platforms.
    The external platform 10 of the upstream distributor 9 has a recess 12 delimiting a support zone formed by a radially external rim 13, extending axially downstream.
    The downstream end of the rim 13 bears axially on the rim 8 of the upstream flange 4 of the casing 2, said rim 13 is also in axial support on the second part 7 of the upstream flange 4.
    The turbine 1 further comprises a ring 14 comprising an abradable material, fixedly mounted on the casing 2 and formed of several contiguous angular sectors 15, identical and distributed over the entire circumference. Each sector comprises a block of abradable material 16.
    The ring formed by the different blocks 16 of abradable material comprises a first annular groove 17, having a first radial dimension or depth and opening at a radially internal cylindrical surface 18 of the ring, and two second annular grooves 19, each having a second radial dimension or depth and opening at the level of said radially internal surface 18.
    The two second grooves 19 are offset axially on either side of the first groove 17.
    The external surface of the block 16 of each sector 15 is fixed to a support 20 of annular shape.
    An annular fixing member 21 with a U-section is fixed at the upstream end of the support 20, radially inside said support 20. Said upstream fixing member 21 comprises a radially external branch 22, coming radially to bear on the external surface of the second part 7 of the upstream flange 4, and a radially internal branch 23 coming radially to bear on the rim 13 of the upstream distributor 10. A rotational coupling member 24 is fixed to the internal branch 23 and is engaged in the recess 12 of the external platform 10 of the upstream distributor 9, so as to immobilize in rotation the sector 15 relative to the upstream distributor 9 and to the casing 2.
    The upstream distributor 10 is thus fixed on the upstream flange 4 using the upstream fixing member 21. This member also makes it possible to fix the support 20 on the upstream flange 4.
    An annular fixing member with a U-section or localized members such as hooks 25 with a U-section are fixed at the level of an axially median zone of the support 20, radially outside said support 20. Said fixing members 25, which will be referred to below as downstream fastening members, comprise a radially external branch 26 and a radially internal strip 27, capable of coming to bear respectively on the radially external surface and the radially internal surface of the downstream flange 5.
    The downstream fixing members 25 thus make it possible to fix the support 20 on the downstream flange 5 of the casing 2.
    The turbine 1 further comprises a rotor wheel comprising a disc 28 (FIG. 2) at the periphery of which blades are mounted 29, the radially outer periphery of each blade comprises a platform 30 comprising a first wiper 31, axially central, and two second wipers 32 offset axially on either side of the first wiper 31. The first and second wipers 31, 32 extend radially outward, the first wiper 31 extending radially outward relative to the second wipers 32. The first wiper 31 is engaged in the first groove 17, the second wipers 32 being engaged in the second grooves 19.
    The axial dimension of the grooves 17, 19 allows a displacement or an uncertainty of axial positioning of the rotor wheel, and therefore of the wipers 31, 32, relative to the casing 2, such uncertainty may be due to manufacturing and mounting tolerances as well as mechanical and / or thermal stresses in operation.
    The mounting of such a turbine 1 is carried out as follows.
    First of all the upstream distributor 9 is mounted inside the casing 2, on the one hand, and the sectors 15 are mounted around the blades 29 so as to form the ring 14 of abradable material.
    The assembly comprising the rotor wheel comprising the disc 28 and the blades 29, as well as the ring 14 formed by said sectors 15, is then engaged axially inside the casing 2, so that the fixing members 21 are engaged axially on the upstream flange 4 and on the flanges 13 of the upstream distributor 9, and that the downstream fixing members 25 are engaged axially on the downstream flange 5, thus ensuring both the fixing of the upstream distributor 9 and the various sectors 15 on the housing
    2.
    FIG. 6 represents an alternative embodiment which differs from that previously exposed in that the ring formed by the blocks 16 is devoid of second grooves 19, the second wipers 32 coming opposite the radially internal cylindrical surfaces 18 of the blocks 16 of material abradable.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Turbine (1) for a turbomachine, in particular for an airplane turbojet or turboprop, comprising a casing (2) and a rotor comprising vanes (29), the radially outer periphery of which comprises at least one first wiper (31) s extending radially outwards, sealing means extending radially around the blades (29) and comprising a ring (14) of abradable material, the radially external ends of the first wipers (31) being engaged in a groove ( 17) of said ring (14) of abradable material so as to form a labyrinth-type seal, characterized in that said ring (14) is formed from several contiguous angular sectors (15), each ring sector (15) comprising at at least one fixing member (21, 25) cooperating with at least one additional hooking flange (4, 5) of the casing (2) so as to assemble each sector (15) on the casing (2) by displacement axial of said sector (15) relative to the casing (2).
    [2" id="c-fr-0002]
    2. Turbine (1) according to claim 1, characterized in that each flange (4, 5) comprises a first part (6) extending radially from a cylindrical or frustoconical wall (3) of the casing (2), and a second part (7) extending axially, cooperating with the fixing member (21, 25) of the corresponding ring sector (15).
    [3" id="c-fr-0003]
    3. Turbine (1) according to claim 1 or 2, characterized in that each fixing member (21, 25) has a general U-shaped section comprising branches (22, 23; 26, 27) extending axially and spaced apart radially from one another, engaging on either side of an axial part (7) of the flange (4, 5) for additional attachment.
    [4" id="c-fr-0004]
    4. Turbine (1) according to one of claims 1 to 3, characterized in that it comprises at least a first fixing member (21) and at least a second fixing member (25), axially offset one relative to each other, capable of cooperating respectively with a first flange (4) and a second flange (5) of the casing (2).
    [5" id="c-fr-0005]
    5. Turbine (1) according to one of claims 1 to 4, characterized in that each ring sector (15) comprises a block (16) of abradable material fixed to a support (20), each fixing member ( 21, 25) being formed by said support (20) or fixed to said support (20).
    [6" id="c-fr-0006]
    6. Turbine (1) according to one of claims 1 to 5, characterized in that each blade (29) comprises at least a first wiper (31) extending radially and at least a second wiper (32) extending radially outside with respect to the first wiper (31), the first wiper (31) and the second wiper (32) being offset axially with respect to each other.
    [7" id="c-fr-0007]
    7. Turbine (1) according to claim 6, characterized in that the first wiper (31) is engaged in a first groove (17) of the corresponding ring sector (15), the second wiper (32) being engaged in a second groove (19) of the ring sector (15).
    [8" id="c-fr-0008]
    8. Turbine (1) according to claim 6, characterized in that the first wiper (31) is engaged in a first groove (19) of the corresponding ring sector (15), the radially outer end of the second wiper ( 32) being located near a surface (18) in a cylinder portion of the ring sector (15).
    [9" id="c-fr-0009]
    9. Turbine (1) according to one of claims 1 to 8, characterized in that it comprises a distributor (9), comprising a radially external platform (10), bearing on a flange (4) of the casing ( 2), the sector (15) comprising a fixing member (21) which fixes the external platform (10) of the distributor (9) on the corresponding flange (4) of the casing (2), while ensuring the fixing of the sector (15) on said flange (4).
    [10" id="c-fr-0010]
    10. A method of mounting a turbine (1) according to one of claims 1 to 9, characterized in that it comprises the steps consisting in:
    - mount the sectors (15) around the blades (29) so as to form the ring (14) of abradable material,
    - Axially engaging the assembly comprising in particular the blades (29) and said sectors (15) in the casing (2), so as to
    5 that the fixing members (21, 25) of the sectors (15) cooperate with the flanges (4, 5) so as to ensure the fixing of said sectors (15) in the casing (2), around the blades (29) .
    1/4
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    同族专利:
    公开号 | 公开日
    US10907505B2|2021-02-02|
    GB201718654D0|2017-12-27|
    GB2558071B|2021-07-14|
    FR3058756B1|2020-10-16|
    GB2558071A|2018-07-04|
    US20180156070A1|2018-06-07|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0844369A1|1996-11-23|1998-05-27|ROLLS-ROYCE plc|A bladed rotor and surround assembly|
    US20050002780A1|2003-07-04|2005-01-06|Ishikawajima-Harima Heavy Industries Co., Ltd.|Turbine shroud segment|
    FR2879649A1|2004-12-22|2006-06-23|Gen Electric|REMOVABLE ABRASIVE JOINT SUPPORTS FOR SEALING BETWEEN ROTARY AND FIXED TURBINE ORGANS.|
    WO2013156734A1|2012-04-20|2013-10-24|Snecma|Turbine stage for a turbomachine|
    FR3007065A1|2013-06-14|2014-12-19|Snecma|ABRADABLE RING FOR TURBOMACHINE|EP3591178A1|2018-07-03|2020-01-08|Safran Aircraft Engines|Aircraft turbine engine sealing module|
    FR3103209A1|2019-11-20|2021-05-21|Safran Aircraft Engines|Labyrinth seal comprising a sliding abradable element|FR2552159B1|1983-09-21|1987-07-10|Snecma|DEVICE FOR CONNECTING AND SEALING TURBINE STATOR BLADE SECTIONS|
    US7334984B1|2003-12-24|2008-02-26|Heico Corporation|Turbine shroud assembly with enhanced blade containment capabilities|
    JP5546420B2|2010-10-29|2014-07-09|三菱重工業株式会社|Turbine|
    WO2014168804A1|2013-04-12|2014-10-16|United Technologies Corporation|Blade outer air seal with secondary air sealing|
    FR3036435B1|2015-05-22|2020-01-24|Safran Ceramics|TURBINE RING ASSEMBLY|FR3065482B1|2017-04-20|2019-07-05|Safran Aircraft Engines|SEAL RING MEMBER FOR TURBINE COMPRISING A CAVITY INCLINED IN ABRADABLE MATERIAL|
    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-18| PLSC| Publication of the preliminary search report|Effective date: 20180518 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661045|2016-11-15|
    FR1661045A|FR3058756B1|2016-11-15|2016-11-15|TURBINE FOR TURBOMACHINE|FR1661045A| FR3058756B1|2016-11-15|2016-11-15|TURBINE FOR TURBOMACHINE|
    GB1718654.5A| GB2558071B|2016-11-15|2017-11-10|Turbine for turbine engine|
    US15/812,117| US10907505B2|2016-11-15|2017-11-14|Turbine for a turbine engine and method of assembling same|
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