• 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 rotor comprising vanes (35) whose radially outer periphery comprises at least a first radially extending lug (39). outwardly, sealing means extending radially around the blades and having a ring of abradable material (20, 21), the radially outer ends of the wipers (39) cooperating with said ring of abradable material so as to form a labyrinth type seal, characterized in that said ring comprises at least a first portion (20) extending axially upstream of the first wiper (39) and a second portion (21) extending axially downstream of the first wiper, (39) the first portion (20) and / or the second portion (21) having a groove (23, 31) into which the first wiper (39) is inserted.
    公开号:FR3058755A1
    申请号:FR1661044
    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；Arnaud Fabien Lambert Olivier
    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.
    104 / TURBINE FOR TURBOMACHINE.
    FR 3 058 755 - A1 _ The invention relates to a turbine (1) for a turbomachine, in particular for an airplane turbojet or turboprop, comprising a rotor comprising vanes (35) whose radially external periphery comprises at least one first wiper (39) extending radially outwards, sealing means extending radially around the blades and comprising a ring of abradable material (20, 21), the radially external ends of the wipers (39) cooperating with said ring of abradable material so as to form a labyrinth type seal, characterized in that said ring comprises at least a first part (20) extending axially upstream of the first wiper (39) and a second part (21) s' extending axially downstream of the first wiper, (39) the first part (20) and / or the second part (21) comprising a groove (23, 31) in which the first wiper (39) is inserted.
    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 effectiveness of such labyrinth seals.
    The object of the invention is in particular to provide a simple, effective and economical solution to this problem.
    To this end, it offers a turbine for a turbomachine, in particular for an airplane turbojet or turboprop, comprising a rotor comprising vanes whose radially external periphery comprises at least one first wiper extending radially outward, means sealing extending radially around the blades and comprising a ring of abradable material, the radially external ends of the wipers cooperating with said ring of abradable material so as to form a seal of labyrinth type, characterized in that said ring comprises at least a first part extending axially upstream of the first wiper and a second part extending axially downstream of the first wiper, the first part and / or the second part comprising a groove in which the first wiper is inserted.
    In this way, 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 structure in two parts of the ring.
    The first part may include a groove opening radially outward and axially downstream, the second part comprising a groove opening radially outward and axially upstream, facing the throat of the first part.
    The radially outer periphery of the blades may include at least one second wiper extending radially, the first wiper extending radially outward from the second wiper.
    The second wiper is able to cooperate with the first part and / or with the second part of the ring. This further increases the pressure losses, and therefore the effectiveness of the labyrinth seal between the blades and the ring of abradable material.
    The first part and / or the second part may comprise means for fixing to an annular turbine casing, capable of fixing the corresponding part of the ring by axial engagement of the downstream upstream on flanges of said casing.
    In this case, each flange may comprise a part extending radially from a cylindrical or frustoconical wall of the casing, and a part extending axially, cooperating with the first part or the second part of the ring.
    Each part of the ring may include a block of abradable material, mounted on an annular support.
    Each support may comprise at least one fixing member of general U-shaped section, capable of cooperating with a flange of the casing so as to secure the support to the casing.
    The turbine may include an upstream distributor comprising a radially external platform, bearing on an upstream flange of the casing, the support of the first part of the ring comprising an upstream fixing member coming to fix the external platform of the upstream distributor on the upstream flange of the casing, while ensuring the fixing of the support of the first part of the ring on said upstream flange.
    The support of the second part of the ring may include an upstream fixing member which fixes the support of the first part of the ring on a central flange of the casing, while ensuring the fixing of the support of the second part of the ring on said middle flange.
    The turbine may comprise a downstream distributor comprising a radially external platform, engaged axially on a downstream flange of the casing, said external platform of the downstream distributor being able to fix the support of the second part of the ring on the downstream 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:
    (a) mounting the first part of the ring on a casing of the turbine, by axial engagement of the downstream upstream of said first part with respect to the casing, (b) mounting the movable wheel in the casing, ( c) mounting the second part of the ring on the turbine casing, by axial engagement from downstream to upstream of said second part relative to the casing, the first wiper being introduced into the groove of the first part and / or the second part during step (b) and / or during step (c).
    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,
    - Figures 2 to 6 illustrate different stages of mounting the turbine of Figure 1.
    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, 6 extend radially inwards. The casing 2 comprises in particular an upstream flange 4, a middle flange 5 and a downstream flange 6. The terms upstream and downstream are defined by reference to the direction F of flow of the gas flow within the turbine 1, that is i.e. from left to right in Figure 1.
    Each flange 4, 5, 6 has a first annular part 7 extending radially inwards from the frustoconical wall 3, and a second cylindrical part 8 extending downstream.
    The upstream flange 4 further comprises an annular radial flange 9 extending radially inwards from the downstream end of the second part 8.
    The stator of the turbine 1 notably comprises two distributor stages, which will be designated respectively upstream distributor 10 and downstream distributor 11, each distributor 10, 11 comprising a radially internal platform (not visible), a radially external platform 12 and fixed blades 13 connecting said platforms.
    The external platform 12 of the upstream distributor 10 has a generally frustoconical wall 14, the downstream end of which comprises a support zone 15 comprising a first part 16 extending radially outwards and a second part 17 extending axially downstream.
    The downstream end of the second part 17 of the support zone 15 bears axially on the flange 9 of the upstream flange 4 of the casing 2, the second part 17 of the support zone 15 being furthermore in axial support on the second part 8 of the upstream flange 4.
    The upstream end of the external platform 12 of the downstream distributor 11 has two flanges 18, 19 extending axially upstream, radially spaced from one another. The radially internal rim 18 bears radially on the radially external surface of the second part 8 of the downstream flange 6. The function of the radially internal rim 18 will be better described below.
    The turbine 1 also comprises a ring comprising an abradable material, fixedly mounted on the casing 2 and formed in two parts 20, 21, namely an upstream part 20 and a downstream part 21.
    The upstream part 20 comprises in particular an upstream block 22 of abradable material, of annular shape. The upstream block 22 has a groove 23 at its downstream end, said groove 23 opening radially inward and axially downstream.
    The external surface of the upstream block 22 is fixed to an upstream support 24, of annular shape. The upstream support 24 has a flange 25 extending radially outward at its downstream end and a flange 26 extending radially outward from a central region of said upstream support 24.
    The upstream support 24 is capable of coming to bear radially on the second part 8 of the middle flange 5, the flanges 25 and 26 of the upstream support 24 being able to come to bear axially on the upstream and downstream ends of the second part 8 of the middle flange 5.
    An annular fixing member 27 with U-section is fixed at the upstream end of the upstream support 24, radially inside said upstream support 24. Said upstream fixing member 27 comprises a radially external branch 28, coming radially in bearing on the external surface of the second part 8 of the upstream flange 4, and a radially internal branch 29 radially bearing on the second part 17 of the bearing zone 15 and on the edge of the upstream flange 4.
    The upstream distributor 10 is thus fixed on the upstream flange 4 using the upstream fixing member 27. This member 27 also makes it possible to fix the upstream support 24 on the upstream flange 4.
    The downstream part 21 of the ring comprises a downstream block 30 of abradable material, of annular shape. The downstream block 30 has a groove 31 at its upstream end, said groove 31 opening radially inward and axially upstream.
    The external surface of the downstream block 30 is fixed to a downstream support 32, of annular shape. The downstream support 32 has a flange 33 extending radially outwards at its downstream end, extended by a cylindrical fixing zone 34 extending axially downstream from the external periphery of the flange 33.
    An annular fixing member with a U-section or localized members such as hooks with a U-section 35 are fixed at the upstream end of the downstream support 32, radially outside said downstream support 32. Said fixing members downstream 35 comprise a radially external branch 36, bearing radially on the external surface of the second part 8 of the middle flange 5, and a radially internal branch 37 bearing radially on the downstream end of the upstream support 24.
    Furthermore, the fixing zone 34 is supported on the internal surface of the second part 8 of the downstream flange 6.
    As indicated previously, the radially external rim 19 of the external platform 12 of the downstream distributor 11 is in radial abutment on the radially external surface of the second part 8 of the downstream flange 6, the radially internal rim 18 of said platform external 12 being supported on the fixing zone 34 of the downstream part 21 of the ring, so as to fix said downstream part 21 of the ring on the downstream flange 6 of the casing
    2.
    The turbine 1 further comprises a rotor wheel comprising vanes 38, the radially outer periphery of each blade 38 comprising a first wiper 39, axially central, and two second wipers 40 offset axially on either side of the first wiper 39 The first and second wipers 39, 40 extend radially outwards, the first wiper 39 extending radially outward relative to the second wipers 40. The first wiper 39 is engaged in the grooves 23, 31 of the upstream and downstream parts 20, 21 of the ring. The second wipers 40 extend opposite the radially internal surfaces of the upstream and downstream blocks 22, 30.
    The cumulative axial dimension of the grooves 23, 31 allows a displacement or an uncertainty of axial positioning of the rotor wheel, and therefore of the first wiper 39, with respect to the casing 2, such uncertainty may be due to manufacturing and manufacturing tolerances. mounting as well as mechanical and / or thermal constraints during operation.
    The mounting of such a turbine 1 is carried out as follows.
    First of all the upstream distributor 10 is mounted inside the casing 2, then the upstream part 20 of the ring is engaged axially from downstream to upstream in the casing 2, on the upstream and middle flanges 4 5 of the casing 2. The upstream fixing member 27 is engaged on the upstream flange 4 and on the part 17 of the upstream distributor 10 so as to secure the upstream distributor 10 on the upstream flange 4. The rotor wheel comprising the blades 38 is then axially engaged in the casing 2, from downstream to upstream, the first wiper 39 being located, at least partially, in the groove 23 of the upstream abradable block 22. The second part 21 of the ring is then axially engaged in the casing 2, from downstream to upstream, the downstream fixing members 35 cooperating with the middle flange 5 and with the downstream end of the upstream support 24, as indicated above. The upstream support 24 is thus fixed on the middle flange 5 by means of said downstream fixing members 35.
    The downstream distributor 11 is then axially engaged in the casing 2, from downstream to upstream, the flanges 18, 19 of the external platform of said downstream distributor 11 coming to cooperate with the downstream flange 6 and with the fixing zone. 34 of the downstream support 32, as indicated previously. The downstream support 32 is thus fixed to the downstream flange 6 of the casing 2, using the downstream distributor 11.
    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 rotor comprising vanes (38), the radially outer periphery of which comprises at least one first wiper (39) extending radially towards the exterior, sealing means extending radially around the blades and comprising a ring of abradable material (20, 21), the radially external ends of the wipers (39) cooperating with said ring of abradable material so as to form a seal of labyrinth type, characterized in that said ring comprises at least a first part (20) extending axially upstream of the first wiper (39) and a second part (21) extending axially downstream of the first wiper (39 ), the first part (20) and / or the second part (21) comprising a groove (23, 31) in which the first wiper (39) is inserted.
    [2" id="c-fr-0002]
    2. Turbine (1) according to claim 1, characterized in that the radially outer periphery of the blades (38) comprises at least a second wiper (40) extending radially, the first wiper (39) extending radially to the exterior with respect to the second wiper (40).
    [3" id="c-fr-0003]
    3. Turbine (1) according to claim 1 or 2, characterized in that the first part (20) has a groove (23) opening radially outward and axially downstream, the second part (21) comprising a groove (31) opening radially outward and axially upstream, opposite the groove (23) of the first part (20).
    [4" id="c-fr-0004]
    4. Turbine (1) according to one of claims 1 to 3, characterized in that the first part (20) and / or the second part (21) comprise fixing means (27, 35) on an annular casing ( 2) turbine, capable of fixing the corresponding part (20, 21) of the ring by axial engagement from downstream to upstream on flanges (4, 5, 6) of said housing (2).
    [5" id="c-fr-0005]
    5. Turbine (1) according to claim 4, characterized in that each flange (4, 5, 6) comprises a part (7) extending radially from a cylindrical or frustoconical wall (3) of the casing (2), and an axially extending part (8) cooperating with the first part (20) or the second part (21) of the ring.
    [6" id="c-fr-0006]
    6. Turbine (1) according to one of claims 1 to 5, characterized in that each part (20, 21) of the ring comprises a block of abradable material (22, 30), mounted on an annular support (24 , 32), each support (24, 32) comprising at least one fixing member (27, 35) of general U-shaped section, capable of cooperating with a flange (4, 5) of the casing (2) so as to ensure the fixing the support (24, 32) to the housing (2).
    [7" id="c-fr-0007]
    7. Turbine (1) according to claim 6, characterized in that it comprises an upstream distributor (10) comprising a radially external platform (12), bearing on an upstream flange (4) of the casing (2), the support (24) of the first part (21) of the ring comprising an upstream fixing member (27) which fixes the external platform (12) of the upstream distributor (10) on the upstream flange (4) of the casing (2), while securing the support (24) of the first part (20) of the ring on said upstream flange (4).
    [8" id="c-fr-0008]
    8. Turbine (1) according to claim 6 or 7, characterized in that the support (32) of the second part (21) of the ring comprises an upstream fixing member (35) coming to fix the support (24) of the first part (20) of the ring on a middle flange (5) of the housing (2), while ensuring the fixing of the support (32) of the second part (21) of the ring on said middle flange (5 ).
    [9" id="c-fr-0009]
    9. Turbine (1) according to one of claims 6 to 8, characterized in that it comprises a downstream distributor (11) comprising a radially external platform (12), engaged axially on a downstream flange (6) of the casing (2), said external platform (12) of the downstream distributor (11) being able to fix the support (32) of the second part (21) of the ring on the downstream flange (6).
    [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:
    (a) mount the first part (20) of the ring on a casing (2)
    5 of the turbine (1), by axial engagement from downstream to upstream of said first part (20) relative to the casing (2), (b) mounting the movable wheel (38) in the casing (2) , (c) mount the second part (21) of the ring on the casing (2) of the turbine (1), by axial engagement from downstream to upstream of
    10 said second part (21) relative to the casing (2), the first wiper (39) being introduced into the groove (23, 31) of the first part (20) and / or of the second part (21) during step (b) and / or during step (c).
    1/2
    15.16
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    FR3058755B1|2020-09-25|
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    GB201718664D0|2017-12-27|
    GB2558072B|2021-06-09|
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    FR3021349B1|2014-05-22|2021-07-02|Herakles|METHOD OF MANUFACTURING A TURBOMACHINE VANE FROM COMPOSITE MATERIAL, THUS OBTAINED VANE AND TURBOMACHINE INCORPORATING IT|
    FR3040461B1|2015-09-02|2018-02-23|Safran Aircraft Engines|LABYRINTH SEALING ELEMENT FOR TURBINE|
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    US10774670B2|2017-06-07|2020-09-15|General Electric Company|Filled abradable seal component and associated methods thereof|DE102019216646A1|2019-10-29|2021-04-29|MTU Aero Engines AG|BLADE ARRANGEMENT FOR A FLOW MACHINE|
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    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
    FR1661044A|FR3058755B1|2016-11-15|2016-11-15|TURBINE FOR TURBOMACHINE|
    FR1661044|2016-11-15|FR1661044A| FR3058755B1|2016-11-15|2016-11-15|TURBINE FOR TURBOMACHINE|
    GB1718664.4A| GB2558072B|2016-11-15|2017-11-10|Turbine for a turbine engine|
    US15/811,986| US10633984B2|2016-11-15|2017-11-14|Turbine for a turbine engine|
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