• 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, comprising a stator and a rotor comprising a rotor wheel (51) comprising vanes (52) whose radially outer periphery comprises at least one wiper (54) extending radially towards outside, sealing means extending radially around the blades (52) and having a ring (19), the radially outer end of the wiper (54) cooperating with said ring (19) so as to form a labyrinth type joint,
    公开号:FR3068070A1
    申请号:FR1755821
    申请日:2017-06-26
    公开日:2018-12-28
    发明作者:Arnaud Fabien Lambert Olivier；Robert Drouet Franck；Frederic Claude Cyrille Evain Gael
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Turbine for turbomachine
    FIELD [001] The present invention relates to a turbine for a turbomachine, in particular for an aircraft turbojet or turboprop, as well as a method for mounting such a turbine.
    BACKGROUND 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 turbine. pressure.
    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 a paddle wheel 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 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 10, while facilitating the assembly and the structure of the assembly.
    The invention particularly aims to provide a simple, effective and economical solution to this problem.
    SUMMARY OF THE INVENTION To this end, the present invention relates to a turbine for a turbomachine, for example for an airplane turbojet or turboprop, comprising a stator, a rotor comprising a rotor wheel comprising blades the radially external periphery comprises at least one wiper extending radially outward, sealing means extending radially around the blades and comprising a sealing ring, the radially external end of the wiper cooperating with said ring d sealing in order to form a labyrinth type seal, characterized in that said sealing ring comprises at least a first part, and a second part, axially offset with respect to each other, the first part and / or the second part delimiting a groove in which the wiper is inserted, the first part comprising a first engaged projecting zone by complementarity of shape in the axial direction in a first hollow zone of the second part, the stator comprising means for holding in position the first and the second part relative to the stator.
    In this way, it is possible to have a wiper which forms a labyrinth type seal with the walls of the groove, said seal having a greater pressure drop than in the case of the prior art. Indeed, thanks to the mounting made possible by the structure in two parts of the ring it is possible to have a first wiper which is of large radial dimension, engaged in a groove of large radial dimension also. In addition, the protruding and recessed areas are configured so as to fit into each other in the axial direction, which makes it possible to guarantee the seal between the first and second parts of the sealing ring. .
    The assembly mentioned above between the first and the second part is thus of the tenon-mortise type.
    [013] The means for holding in position may comprise a stop for radial support of the first part and a means for clamping the second part against the stator, the first part being arranged upstream of the second part.
    [014] Such a characteristic makes it easier to mount the ring on the stator.
    The first part may include a recess opening radially outward and axially downstream, the second part comprising a recess opening radially outward and axially upstream, opposite the recess of the first part . The recesses of the first and second parts then form the groove. Alternatively, only one of the first and second parts can have a recess, the groove being delimited by said recess and by a radial surface of the opposite part.
    The first part can be held radially, upstream, by the stator, the first part being held radially, downstream, by the second part.
    The first part and the second part may comprise a block of abradable material mounted on a support, the first projecting and recessed areas of said first and second parts being formed on the supports.
    The first part and the second part may be annular and may be formed of a succession of ring sectors, each ring sector having slots at its circumferential ends, sealing tongues being mounted in said slots between said sectors.
    The first protruding area and the first recessed area may extend circumferentially over an angular range less than or substantially equal to the circumferential extension of a sector of the sealing ring. As indicated above, the first protruding area and the first hollow area form a baffle limiting the rate of leakage of gases flowing in the vein radially outward, between the first and second parts. In order to maximize the effectiveness of such a baffle, it is preferable that it extends circumferentially over all or almost all of the circumferential extension of a ring sector. The aforementioned circumferential extension makes it possible to limit this leakage rate as much as possible.
    The first part, or respectively the second part, may include a second projecting zone engaged by complementary shape in a second hollow zone of the second part, or respectively of the first part, the first projecting zones and hollow being offset radially from the radially internal surface of the second protruding and hollow areas.
    [022] More particularly, the first protruding and recessed areas can be offset radially outward relative to the second protruding and recessed areas.
    The first projecting area or the first recessed area can be offset axially with respect to the second projecting area or the second recessed area.
    Thanks to this axial offset, the baffle is enlarged in the axial direction, which contributes to maximizing the efficiency of the baffle by effectively limiting the gas leakage rate between the first part and the second part of the ring sealing.
    [025] The stator may comprise a turbine casing comprising an annular wall, for example frustoconical, at least one flange extending radially inwards from the annular wall of the turbine casing, said flange bearing axially, at the upstream, on a radially external annular rim of the first part, said flange bearing axially, downstream, on a radially external annular rim of the second part.
    Said flanges can be formed in the supports of the first and second parts.
    [027] The stator may include a downstream distributor, the downstream end of the second part being engaged in a groove in the downstream distributor.
    [028] The turbine housing flange can also be engaged in the groove of the downstream distributor [029] Each projecting zone can be attached to the first part or to the second part, at its base, and can have one end free opposite the base. The first protruding area can belong to the first part, or respectively to the second part, the second protruding area can belong to the second part, or respectively to the first part. In this case, the free end of the first protruding area can be offset axially relative to the base of the second protruding area. Furthermore, the free end of the second projecting zone can be offset axially with respect to the base of the first projecting zone. The base of the first protruding area may be located axially opposite the base of the second protruding area.
    The block of abradable material of the first part may include a downstream radial surface. The block of abradable material of the second part may include a radial upstream surface. The blocks of abradable material of the first and second parts can be in contact with one another at the level of said radial downstream and upstream surfaces. [031] The base of the second projecting zone can be offset axially, for example downstream, relative to the downstream surface of the block of the first part and / or relative to the upstream surface of the block of the second part . The first part and / or the second part has a radially outer surface intended to support the housing flange.
    Said external support surface has at least one annular groove. In this way, the contact area between the housing flange and the first and second parts is limited, so as to guarantee correct positioning.
    [034] The part may include a fixing member, for example of U-shaped cross section, engaged by shape complementarity on the stator. The fixing member can be fixed to the support of the first part.
    Each blade of the rotor wheel can comprise at least a first wiper and a second wiper, the first wiper extending radially outwards, beyond the second wiper. The first wiper can be engaged in the groove defined by the first and second parts. The second wipers can cooperate with radially internal and cylindrical or frustoconical surfaces of the first and second parts.
    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 on a casing of the turbine, by axial engagement of the downstream upstream of said first part relative to the casing, (b) mounting the rotor wheel in the casing, (c) mounting the second part on the first part, by axial engagement of the downstream to upstream of said second part relative to the first part, the wiper being introduced into the groove during step (b) and / or during step (c).
    BRIEF DESCRIPTION OF THE FIGURES [037] 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 accompanying drawings.
    - Figure 1 is an axial sectional view of part of a turbine according to an embodiment of the invention, Figures 2 to 4 are exploded views, in perspective, of a part of the turbine according to l 'invention;
    Figures 5 to 9 are views in axial section of a part of the turbine, illustrating the successive stages of the mounting method according to the invention.
    DETAILED DESCRIPTION [038] A low-pressure turbine 1 of a turbomachine according to one 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 F of flow of the gas flow within the turbine 1, that is to say of left to right in Figure 1.
    [039] Each flange 4, 5 comprises a first annular part 6 extending radially inwards from the frustoconical wall 3, and a second cylindrical part 7 extending downstream.
    [040] The upstream flange 4 further comprises an annular radial flange 8 extending radially inwards from the downstream end of the second part 7.
    [041] The stator of the turbine 1 comprises in particular two distributor stages, which will be designated respectively upstream distributor 9 and downstream distributor 10, each distributor 9, 10 comprising a radially internal platform (not visible), a platform radially external 11a, 11b and fixed blades 12a, 12b connecting said platforms.
    [042] The external platform 11a of the upstream distributor 9 has a generally frustoconical wall 13, the downstream end of which comprises a support zone 14 comprising a first part 15 extending radially outwards and a second part 16 s 'extending axially downstream.
    [043] The downstream end of the second part 16 of the support zone 14 bears axially on the flange 8 of the upstream flange 4 of the casing 2, the second part 16 of the support zone 14 being further in axial support on the second part 7 of the upstream flange 4.
    [044] The upstream end of the external platform 11 of the downstream distributor 10 has a radially internal rim 17 and a radially external rim 18 extending axially upstream, radially spaced from one another. The radially outer rim 18 bears radially on the radially outer surface of the second part 7 of the downstream flange 5. The function of the radially inner rim 17 will be better described below.
    The turbine 1 further comprises a sealing ring 19, fixedly mounted on the casing 2 and formed in two parts 20, 36, namely an upstream part 20 and a downstream part 36. The sealing ring 19 is formed by several angular sectors 21 contiguous over the entire circumference, also visible in FIGS. 2 to 4.
    [046] The upstream part 20 comprises in particular an upstream block 22 of abradable material, of annular shape. The upstream block 22 has a recess 23A at its downstream end, said recess 23A opening radially inward and axially downstream.
    [047] The external surface of the upstream block 22 is fixed to an upstream support 24, of annular shape. The upstream support and the upstream block are thus segmented. The upstream support 24 has a flange 25 located in a central region of the support 24 and extending radially outwards. The flange is capable of coming to bear axially on the downstream flange of the casing.
    [048] The radially outer surface of the upstream support 24 further comprises an annular groove 26 located directly downstream of the rim 25. The downstream end of the upstream support 24 forms an annular support area 27 of limited surface, able to come in radially supported on the downstream flange 5 of the casing 2.
    [049] The upstream support 24 includes a recessed area 28 on its radially inner part, said recessed area 28 opening radially inward and axially downstream.
    [050] The upstream support 24 further comprises a projecting area 29 extending axially downstream and extending circumferentially over almost the entire sector 21 concerned.
    [051] The protruding area 29 has a base 30 located upstream and a free end 31 opposite the base, located downstream.
    [052] The protruding area 29 is offset radially outward with respect to the recessed area 28. Furthermore, the base 30 of the protruding area 29 is offset axially downstream from the upstream end 32 of the hollow area 28.
    [053] An annular fixing member 33 with a U-section is fixed at the upstream end of the upstream support 24, radially inside said upstream support 24. Said upstream fixing member 33 comprises a radially external branch 34, coming radially to bear on the external surface of the second part 7 of the upstream flange 4, and a radially internal branch 35 coming radially to bear on the second part 16 of the bearing zone 15 and on the edge of the upstream flange 4 .
    [054] The upstream distributor 9 is thus fixed on the upstream flange 4 using the upstream fixing member 33. This member 33 also makes it possible to fix the upstream support 24 on the upstream flange 4.
    [055] The downstream part 36 comprises in particular a downstream block 37 of abradable material, of annular shape. The downstream block 37 has a recess 23B at its upstream end, said recess 23B opening radially inward and axially upstream. The recesses 23A, 23B of the upstream 22 and downstream blocks 37 delimit a groove 39.
    [056] The external surface of the downstream block 37 is fixed to a downstream support 38, of annular shape.
    [057] The downstream support 38 and the downstream block 37 are thus sectorized. The downstream support 38 has a flange 40 located in a downstream area of the support 38 and extending radially outward. The rim 40 is capable of coming into axial abutment on the downstream flange 5 of the casing 2.
    [058] The radially external surface of the downstream support 38 further comprises an annular groove 41 located upstream of the rim 40. The upstream area of the downstream support 38 forms two annular support zones 42 of limited surfaces, located axially on the side and d other of the groove 41. Said bearing zones are capable of coming to bear radially on the flange 5 downstream of the casing 2. [059] The downstream support 38 comprises a projecting zone 43 on its radially inner part, said zone in projection 43 extending axially upstream and being engaged by complementary shape in the hollow zone 28 of the upstream support 24.
    [060] The downstream support 38 also comprises a hollow area 44 extending circumferentially over almost the entire sector 21 concerned. The projecting area 29 of the upstream support 24 is engaged by complementary shape in the hollow area 44 of the downstream support 38.
    [061] The protruding area 43 of the downstream support 38 comprises a base 45 located downstream and a free end 46 opposite the base 45, located upstream. [062] The protruding area 43 is offset radially inward relative to the recessed area 44. Furthermore, the base 45 of the protruding area is offset axially upstream relative to the downstream end of the recessed area 47.
    [063] Furthermore, the downstream support 38 comes to bear radially on the radially external surface 48 of the internal rim 17 of the external platform 11b of the downstream distributor 10. The downstream block 37 is in axial support on the upstream radial surface of the rim internal 17 of the external platform 11b of the downstream distributor
    10.
    [064] The turbine 1 further comprises a rotor wheel 51 comprising blades 52, the radially outer periphery 53 of each blade 52 comprising a first wiper 54, axially central, and two second wipers 55 offset axially on either side of the first wiper 54. The first and second wipers 54, 55 extend radially outward, the first wiper 54 extending radially outward relative to the second wipers 55. The first wiper 54 is engaged in the recess 23A, 23B of the upstream and downstream parts 20, 36 of the ring
    19. The second wipers 55 extend opposite the radially internal surfaces of the upstream and downstream blocks 22, 37.
    [065] The cumulative axial dimension of the recesses 23A, 23B, that is to say the axial dimension of the groove 39, allows a displacement or an uncertainty of axial positioning of the rotor wheel 51, and therefore of the first wiper 54, 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.
    [066] The mounting of such a turbine 1 will now be described with reference to Figures 5 to 9.
    [067] First of all the upstream distributor 9 is mounted inside the casing 2 (FIG. 5), then the upstream part 20 of the ring 19 is engaged axially from downstream to upstream in the casing 2 (Figure 6), on the upstream flange 4 of the housing
    2. The upstream fixing member 33 is engaged on the upstream flange 4 and on the part 16 of the upstream distributor 9 so as to secure the upstream distributor 9 on the upstream flange 4. The rotor wheel 51 comprising the blades 52 is then axially engaged in the casing 2, from downstream to upstream (FIG. 7), the first wiper 54 being located, at least partially, in the recess 23A of the upstream abradable block 22. The downstream part 36 of the ring 19 is then axially engaged in the casing 2, from downstream to upstream, so that the projecting 29 and hollow 28 areas of the upstream part can engage by form cooperation in the areas hollow 44 and projecting 43 from the downstream part 36 (FIG. 8). The downstream part 36 is thus fixed on the upstream part 20.
    [068] The downstream distributor 10 is then engaged axially in the casing 5 2, from downstream to upstream (FIG. 10). The rim 17 of the external platform of the downstream distributor 10 comes into radial support with the downstream flange 5. The internal rim 7 of the external platform 11b of the downstream distributor 10 comes into radial support on the radially internal surface of the support downstream 38 and bears axially on the downstream block 37, as indicated above. The downstream support 38 is thus kept in abutment with the downstream flange 6 of the casing 2, using the downstream distributor 10.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Turbine (1) for a turbomachine comprising a stator (2, 9, 10) and a rotor comprising a rotor wheel (51) comprising blades (52) whose radially outer periphery comprises at least one wiper (54) s' extending radially outwards, sealing means extending radially around the blades (52) and comprising a sealing ring (19), the radially external end of the wiper (54) cooperating with said ring sealing (19) so as to form a labyrinth type seal, characterized in that said sealing ring (19) comprises at least a first part (20) and a second part (36) offset axially with respect to the other, the first part (20) and / or the second part (36) delimiting a groove (39) in which the wiper (54) is inserted, the first part (20) comprising a first projecting zone (29) engaged by complementary form according to the axi direction ale in a first recessed area (44) of the second part (36), the stator (2, 9, 10) comprising means for holding in position the first and the second part (20, 36) relative to the stator (2, 9, 10).
    [2" id="c-fr-0002]
    2. Turbine (1) according to claim 1, characterized in that the means for holding in position comprise a radial support stop (4, 7) of the first part (20) and a clamping means (17, 18) of the second part (36) against the stator (2, 9, 10), the first part (20) being arranged upstream of the second part (36).
    [3" id="c-fr-0003]
    3. Turbine (1) according to claim 1 or 2, characterized in that the first part (20) is held radially, upstream, by the stator (2, 9, 10), the first part (20) being maintained radially, downstream, by the second part (36).
    [4" id="c-fr-0004]
    4. Turbine (1) according to one of claims 1 to 3, characterized in that the first part (20) and the second part (36) are annular and are formed of a succession of ring sectors (21) , each ring sector (21) having slots at its circumferential ends, sealing tongues being mounted in said slots between said sectors (21).
    [5" id="c-fr-0005]
    5. Turbine (1) according to one of claims 1 to 4, characterized in that the first projecting zone (29) and the first hollow zone (44) extend circumferentially over an angular range less than or substantially equal to the circumferential extension of a sector of the sealing ring (19).
    [6" id="c-fr-0006]
    6. Turbine (1) according to one of claims 1 to 4, characterized in that the first part (20), or respectively the second part (36), comprises a second projecting zone (45) engaged by complementary shape in a second recessed zone (28) of the second part (36), or respectively of the first part (20), the radially internal surface of the first protruding (29) and recessed (44) zones being offset radially with respect to to the radially internal surface of the second projecting (45) and recessed (28) zones.
    [7" id="c-fr-0007]
    7. Turbine (1) according to claim 6, characterized in that the first projecting area (29) or the first recessed area (44) are offset axially with respect to the second projecting area (45) or the second area recessed (28).
    [8" id="c-fr-0008]
    8. Turbine (1) according to one of claims 1 to 7, characterized in that the stator comprises a casing (2) of turbine comprising an annular wall, for example frustoconical (3), at least one flange (5) s extending radially inwards from the annular wall of the turbine casing (2) (1), said flange (5) bearing axially, upstream, on a radially external annular flange (25) of the first part ( 20), said flange (5) bearing axially, downstream, on a radially external annular flange (40) of the second part (36).
    [9" id="c-fr-0009]
    9. Turbine (1) according to one of claims 1 to 8, characterized in that the stator comprises a downstream distributor (10), the downstream end of the second part (36) being engaged in a groove of the downstream distributor ( 10).
    [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) on a casing (2) of the turbine (1), by
    5 axial engagement from downstream to upstream of said first part (20) relative to the casing (2), (b) mounting the rotor wheel (51) in the casing (2), (c) mounting the second part (36) on the first part (20), by axial engagement from downstream to upstream of said second part
    10 (36) relative to the first part (20), (d) the wiper (54) being introduced into the groove (39) during step (b) and / or during step (c).
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    同族专利:
    公开号 | 公开日
    US10760441B2|2020-09-01|
    EP3421730A1|2019-01-02|
    US20190010818A1|2019-01-10|
    FR3068070B1|2019-07-19|
    EP3421730B1|2020-04-29|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3867060A|1973-09-27|1975-02-18|Gen Electric|Shroud assembly|
    FR2879649A1|2004-12-22|2006-06-23|Gen Electric|REMOVABLE ABRASIVE JOINT SUPPORTS FOR SEALING BETWEEN ROTARY AND FIXED TURBINE ORGANS.|
    US20080175706A1|2007-01-09|2008-07-24|Kabushiki Kaisha Toshiba|Steam turbine|
    US20150292347A1|2012-01-03|2015-10-15|General Electric Company|Forward step honeycomb seal for turbine shroud|
    US5653579A|1995-11-14|1997-08-05|Solar Turbines Incorporated|Ceramic blade with tip seal|
    US6036437A|1998-04-03|2000-03-14|General Electric Co.|Bucket cover geometry for brush seal applications|
    DE19821365C2|1998-05-13|2001-09-13|Man Turbomasch Ag Ghh Borsig|Cooling a honeycomb seal in the part of a gas turbine charged with hot gas|
    US6722846B2|2002-07-30|2004-04-20|General Electric Company|Endface gap sealing of steam turbine bucket tip static seal segments and retrofitting thereof|
    US8807927B2|2011-09-29|2014-08-19|General Electric Company|Clearance flow control assembly having rail member|
    FR3058755B1|2016-11-15|2020-09-25|Safran Aircraft Engines|TURBINE FOR TURBOMACHINE|US10934877B2|2018-10-31|2021-03-02|Raytheon Technologies Corporation|CMC laminate pocket BOAS with axial attachment scheme|
    US11008894B2|2018-10-31|2021-05-18|Raytheon Technologies Corporation|BOAS spring clip|
    DE102019216646A1|2019-10-29|2021-04-29|MTU Aero Engines AG|BLADE ARRANGEMENT FOR A FLOW MACHINE|
    法律状态:
    2018-12-28| PLSC| Publication of the preliminary search report|Effective date: 20181228 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 3 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1755821|2017-06-26|
    FR1755821A|FR3068070B1|2017-06-26|2017-06-26|TURBINE FOR TURBOMACHINE|FR1755821A| FR3068070B1|2017-06-26|2017-06-26|TURBINE FOR TURBOMACHINE|
    EP18179383.7A| EP3421730B1|2017-06-26|2018-06-22|Turbine for turbine engine with sealing ring comprising two parts|
    US16/016,882| US10760441B2|2017-06-26|2018-06-25|Turbine for a turbine engine|
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