• 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 rotary assembly for a turbomachine, comprising: - a disc (16) having an outer periphery having an alternation of cells (22) and teeth (20), - blades (14) extending radially from the disc (16) and whose feet (24) are engaged axially and retained radially in the cavities (22) of the disc, - upstream and / or downstream of the disc, an annular sealing flange (52) of cavities (36) formed radially between respectively the blade roots and the bottoms of the disk cells, said flange comprising outer portion (56) arranged axially opposite the upstream and / or downstream ends, respectively, of the disc teeth and blade roots. According to the invention, the assembly further comprises an intermediate ring (66) which is arranged axially between the flange (52) and the teeth (20) of the disc, and also comprises a seal (70) which is arranged axially between, on one side, the intermediate ring (66) and, on the other hand, the teeth (20) of the disc and the blade roots (24).
    公开号:FR3022944A1
    申请号:FR1455997
    申请日:2014-06-26
    公开日:2016-01-01
    发明作者:Stephane Pierre Guillaume Blanchard；Youki Olivier Ito-Lardeau
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to a rotary assembly for a turbomachine, such as in particular an aircraft turbojet, and to a turbomachine comprising such an assembly. Such an assembly, which is found in particular in a turbine, comprises a disk, and blades extending radially outwardly from the disk and whose feet are axially engaged in cells of the outer periphery of the disk, and retained radially by disk teeth arranged alternately with said cells. Cavities known as cell bottom are formed by spaces which are located radially between the blade roots and the bottom of the cells, and which extend axially from upstream to downstream of the cells. These cavities of cell bottom appear particularly in rotation, when the blades, by centrifugal effects, are plated radially outwards against the lateral surfaces of the teeth of the disc. The blades also comprise internal platforms circumferentially arranged end to end so as to together define the internal limit of the flow flow of the hot gases circulating in the turbine. The part of the blade situated internally in relation to the vein, that is to say between the internal platform and the foot, is called stilt. According to this arrangement, spaces are formed between two adjacent stilts, and form inter-stilt or inter-blade cavities. In order to improve the performance of the turbomachine, and to prevent the disk from overheating by the flow of hot gases from an upstream combustion chamber and flowing through the vein, it is important to limit the maximum circulation of these gases through the cavities of cell bottoms, using sealing means. Indeed, the portion of the vein gas flowing into the cell bottom cavities does not participate in the drive in rotation of the blades and directly heats the disk. It is particularly advantageous to arrange the sealing means upstream of the disk teeth and the blade roots, which prevent the flow of vein from reaching the cell bottom cavities. To this end, it is known to use a sealing flange, generally a labyrinth ring, held at an inner portion, generally a radial annular wall, between the flanges of two successive disks of the turbine tying together these latter. The flanges of the discs are conventionally borne by frustoconical walls extending radially inwards and axially on either side of the discs. The sealing flange generally comprises external wipers intended to cooperate with portions of abradable material carried internally by circumferential rows of static vanes arranged through the vein axially alternately with the blades in rotation of the discs. The sealing flange also comprises one or two annular walls, or annular arms, extending outwardly with respect to the disk, from the inner part of the flange to the teeth and to the blade roots of the disks respectively upstream and / or downstream. . The ends of these annular walls are in annular support against the axial end faces of the teeth and blade roots of the respective disks. Thus, the sealing flange protects the discs and cavities of cells from the hot stream of vein. However, this solution is not optimal and has the following defects. In practice, the axial length of the blade roots is different from the axial length of the teeth of the disc. A first axial clearance is thus formed between the respective axial ends of the blade roots and teeth of the disc, due to both manufacturing tolerances and the assembly of blades on the disc. In addition, in rotation, the annular walls of the sealing flange flex radially outwardly around their point of attachment to the disks shown above. The ends of the annular walls of the flange then axially deviate from the teeth of the disc and the blade roots in a second axial play, during this deflection. Vein air can therefore circulate between the flange and the disk / blade assembly, and flow through the cavities of cell bottoms. The present invention provides a simple, effective and economical solution to the problem of sealing cavities cell bottoms, while overcoming the disadvantages associated with the solutions of the prior art. To this end, it proposes a rotary assembly for a turbomachine, comprising: a disk having an outer periphery having an alternation of cells and teeth extending from upstream to downstream of the disk, vanes extending radially from the disk and whose feet are engaged axially in the cells and retained radially by the teeth of the disk, - upstream and / or downstream of the disk, an annular sealing flange of cavities formed radially between respectively the blade roots and the bottoms of the disk cells, said flange comprising an inner portion retained by the disk, and an outer portion arranged in axial relation with the upstream and / or downstream ends, respectively, of the teeth of the disk and of the blade roots, characterized in that it further comprises an intermediate ring which is arranged axially between the flange and the teeth of the disc, and radially between the inner part and the outer part of the disc, and in that it comprises also a seal which is arranged axially between, on one side, the intermediate ring and, on the other hand, the disc teeth and the blade roots, the intermediate ring and the seal being configured to rotate the seal between, on one side, the sealing flange and, on the other hand, the disc teeth and the blade roots. The intermediate ring is preferably configured to cooperate in rotation in annular support with the flange so as to be constrained axially towards the upstream and / or downstream ends, respectively, of the teeth of the disc and the blade roots.
    [0002] The seal is preferably configured to cooperate in rotation in annular support with the intermediate ring so as to be axially pressed against the upstream and / or downstream ends, respectively, of the teeth of the disk and the blade roots.
    [0003] Thus, in rotation, due to the centrifugal forces and thermal expansion of the flange, the outer flange portion axially away from the teeth of the disk and the blade roots. However, the intermediate ring rests on the flange and plates the seal against the teeth of the disc and the blade roots. A complete chain of sealing by annular contact is thus provided between the flange on one side and the disk teeth and blade roots on the other side, through the intermediate ring and the seal . In practice, the axial length of the blade roots is different from the axial length of the teeth of the disc. Axial play is thus formed between the respective axial ends of the blade roots and the teeth of the discs, due to both manufacturing tolerances and the assembly of blades on the disc. It appears that the invention allows the use of a conventional gasket, metal, small enough diameter to allow the seal to deform and come to marry the accident of shape formed by the axial ends of the teeth and feet of blades, so as to eliminate the aforementioned game. The seal, in order to ensure its function under the conditions described above, must indeed have a diameter greater than twice the cumulative total axial clearance. The tightness is therefore assured.
    [0004] Advantageously, the intermediate ring and the seal are split and open radially in rotation. Thus, in rotation, the intermediate ring and the seal open and thus extend radially, and provide respective annular radial supports against the sealing flange and the intermediate ring, so as to optimize the sealing between these parts. Advantageously, the sealing flange has an internal frustoconical surface inclined axially toward the disk and radially outwardly, and arranged in axial and radial relation with the intermediate ring, and on which the intermediate ring rotates . This internal frustoconical surface preferably extends to the axial end of the sealing flange facing the teeth of the disc. The radial support in rotation against such a surface, by centrifugal effects, is sealed, and provides a mechanical reaction that constrains the intermediate ring axially towards the disk. Preferably, the intermediate ring has an outer frustoconical surface axially inclined towards the disk and radially outwardly, and complementary to the frustoconical surface of the sealing flange. The complementarity of the surfaces of the sealing flange and the intermediate ring ensures better annular contact and better sealing between these parts. Advantageously, the intermediate ring comprises an internal frustoconical surface axially inclined towards the disk and radially outwardly, and arranged radially facing the seal, and on which the rotational seal rests. This inner frustoconical surface preferably extends to the axial end of the intermediate ring facing the teeth of the disc. The radial support against such a surface is sealed and provides a mechanical reaction that plates the seal axially against the teeth of the disk and the blade roots.
    [0005] According to another characteristic of interest, the seal is arranged in an annular groove downstream of the intermediate ring. This annular groove then comprises said inner frustoconical wall of the intermediate ring. This groove ensures the maintenance of the seal in all operating conditions of the assembly. In a preferred embodiment, the seal has a diameter of between 0.6 and 1.2 mm, and preferably between 0.8 and 1 mm. The seal may in particular be metallic under these conditions. This diameter is adapted to allow a metal seal to deform and marry irregularities formed by the ends of the disc teeth and blade roots. The seal is therefore optimal. For a better seal, the seal can be hollow. This form coupled to a suitable size allows a better seal because it allows a deformation that closely matches the tooth surfaces of the disk and blade roots.
    [0006] In order to ensure optimum operation, the maximum clearance between the axial ends of the blade roots and the disc teeth must be less than the thickness of the crushed hollow seal. For this purpose, it will be possible to use a hollow joint with a total diameter of about 1 mm, with a central hollow portion with a diameter of about 0.8 mm.
    [0007] Preferably, the intermediate ring and the seal are arranged integrally externally to the cavities of cell bottoms. According to a particular embodiment, the inner portion of the sealing flange is arranged further upstream and / or downstream, respectively, than the outer portion of the sealing flange. The invention also relates to a turbomachine turbine comprising a rotary assembly as described in the present patent application. The invention finally relates to a turbomachine, such as a turbojet engine or a turboprop engine, comprising a rotary assembly as described in the present patent application. Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings, in which: FIG. 1 is a partial diagrammatic view in axial section of a turbomachine low-pressure turbine according to the prior art; Figure 2 is a partial schematic view in axial section of a rotary stage of the turbine according to the prior art, in operation; Figure 3 is a schematic axial sectional view of a rotary assembly according to the invention; Figure 4 is a schematic axial sectional view of a rotary assembly according to the invention, in operation. Reference is first made to FIGS. 1 and 2, which show a low-pressure turbine 10 according to the prior art, arranged downstream of a high-pressure turbine 12. The low-pressure turbine 10 comprises an axial alternation of rows of annular rows. fixed vanes 18, called distributors, and stage of rotating disks 16 having at their peripheries a plurality of vanes 14, these stages being arranged around an axis X of the turbomachine. In this document, as in the technical field concerned, the terms upstream and downstream AV AV are defined so that the upstream is located axially on the side from which the flow of general flow of the turbine engine, and the downstream is located axially on the side towards which this same flow flows. Each disc 16 comprises at its outer periphery teeth (the top of which is referenced 20) arranged alternately with cavities (whose bottom is referenced 22) in which are axially engaged and retained radially blade roots (whose end internal is referenced 24), these vanes 14 extending radially from the cells 22 in an annular flow stream 26 of a hot gas flow from an upstream combustion chamber (not shown). More particularly, each blade comprises radially from the outside towards the inside a blade 28, a platform 30 extending substantially perpendicular to the axis of elongation of the blade 14, and a stag 32 connecting the platform at the blade root 24. The blade roots 24 have a shape for example dovetail or the like to ensure their radial retention in the cells 22. The platforms 30 of the blades are arranged circumferentially end to end so as to together define the ideal internal limit of the flow flow of the hot gases flowing in the turbine. According to this arrangement, spaces are formed between two circumferentially adjacent stilts 32 in the annular zone extending radially from the platforms 30 to the disk 16, and are called inter-stilt or inter-blade cavities 34. so-called cell cavities 36 are also formed by radial spaces separating the blade roots 24 from the bottoms 22 of the cells, and open upstream and downstream of the discs 16. Walls 38, 40 extend radially towards the end interior from the upstream and downstream platforms to the feet 24 of the vanes and form axial sealing means of the annular zone extending radially from the platforms 30 to the disc 16, and therefore inter-blade cavities 34, ensuring their closure.
    [0008] The upstream radial wall 38 of the platform is connected to a spoiler 42 extending upstream and the downstream radial wall 40 is connected to a spoiler 44 extending downstream. The spoilers 42, 44 extend axially between the consecutive stages of the turbine in order to partially preserve the structural integrity of the vein 26 between each turbine stage, which limits the circulation of hot gases radially towards the inside of the turbine. turbine. The discs are secured to each other by bolting, at 46, annular flanges 48, 50 extending axially towards each other from each disc. A labyrinth ring 52, also called a sealing flange, is also positioned axially between each pair of adjacent discs 16 and comprises in an external part two annular walls, or upstream and downstream annular arms 54, 56 extending axially to these discs. The ends of the annular arms are positioned in axial annular support against the teeth of the disks and the blade roots, outside the cavities of cell bottoms, to prevent the vein gases from circulating radially inwards along the teeth of the teeth. discs, and thus reach the cavities of alveolus bottoms.
    [0009] The fastening flanges 48, 50 between the discs are thus also protected from the vein gases by the arms 54, 56 of the labyrinth ring 52 which cover them externally. The labyrinth ring 52 further comprises, in an internal part, an internal radial annular wall 58 for fastening to the bolting 46 of the flanges 48, 50 of the disks, and cooperates with external annular wipers 60 with the inner ends of the vanes 18 of the distributors in order to to limit the axial circulation of the vein gas internally with respect to these blades 18. In order to ensure the proper functioning of the turbomachine, a cooling air A is taken, in a low-pressure or high-pressure compressor, for example, and conveyed by the inner part of the turbine, towards the annular space formed radially between on the one hand the flanges 48, 50 of the disk and on the other hand the arms 54, 56 of the labyrinth rings, to the bottom cavities of cell 36 to ensure the cooling of the disc 16 and to protect the latter from heating caused by the hot gases of the stream of stream 26. In order to allow the circulation of cooling air A downstream of cavities 36 of cell bottom, the latter open downstream internally relative to the arm 54 of the labyrinth ring 52 in axial support on the disk 16. This configuration allows the cooling air A to circulate further downstream radially between the labyrinth ring 52 and the flanges 48, 50 for fixing between the disks 16, in order to also ensure cooling thereof. In operation, as illustrated in FIG. 2 and explained earlier in this document, the annular arms 54, 56 of the labyrinth rings 52 bend outwardly and move axially away from the teeth 20 of the discs and the blade roots 24; which allows the hot gases of the vein to circulate radially inwards along the upstream and downstream faces of the teeth 20 of the discs, and to reach the disc 16 and the cavities of the cell bottoms 36. The prior art, in order to limit this phenomenon, annular hooks (not shown) can be formed upstream and downstream of the stilts, which serve to axially hold the ends of the arms of the labyrinth ring in the vicinity of the teeth of the discs, preventing these extremes too far away from the disks. However, this solution only limits the problem, and does not remove it. The proposed solution, according to the characteristics mentioned above in the present application, is represented in FIGS. 3 and 4. In the embodiment shown, the sealing means according to the invention are formed upstream of the cavities of FIG. bottoms of cells. Equivalently and symmetrically, it is possible to place these sealing means downstream of these cavities. Thus, with reference to FIG. 3, the downstream end of the downstream arm 56 of the labyrinth ring 52 comprises a radial wall 62 extended to the outside by a frustoconical wall 64 inclined radially outwards and axially towards the outside. downstream, and whose outer annular end is, at rest, in contact with the upstream end faces of the teeth 20 of the disc and 15 blade roots 24, disregarding the alignment game between the latter parts . This contact is made more particularly at the radial level of the outer end of the teeth 20 of the disc. A split intermediate ring 66 is arranged axially between the downstream end of the downstream arm 56 of the labyrinth ring 52 and the teeth 20 of the disc, and is sized to contact the latter at rest. This intermediate ring comprises upstream and external surfaces of complementary shapes at the downstream end 62, 64 of the downstream arm 56 of the labyrinth ring, that is to say respectively radial and frustoconical inclined radially outward and axially to downstream. The downstream face 25 of the intermediate ring 66 is plane radially, to ensure good axial support against the teeth 20 of the disk and the blade roots 24, and has an annular axial groove 68 of frustoconical outer surface inclined downstream and the outside. The inner end of the intermediate ring 66 is, for its part, always radially outside the cavities 36 of the cell bottoms. Thanks to the complementarity of shape, the contact is optimal between the intermediate ring. 66 and the arm 56 of the labyrinth ring 52, which ensures a good seal between these two parts. In addition, in rotation, the intermediate ring 66 tends to open radially, due to the centrifugal forces, which by mechanical reaction of radial support against the frustoconical wall 64 of the arm 56 constrains the intermediate ring 66 axially towards the teeth 20 of the disc. In the groove 68 of the intermediate ring is arranged a split metal seal 70 with a diameter of between 0.6 and 1.2 mm, and preferably between 0.8 and 1 mm. This seal 68 may be hollow and also adapted in another type of material. As illustrated in FIG. 4, in operation, identical to the prior art, the arm 56 of the labyrinth ring 52 flexes and deviates axially from the teeth 20 of the disc. However, the mechanical radial support reaction 15 between the intermediate ring 66 and the frustoconical wall 64 of the arm 56 always takes place, and makes the intermediate ring 66 slip along the frustoconical wall 64 of the arm, towards the end. downstream, so as to remain axially against the teeth 20 of the disc, the groove 68 facing the teeth 20 of the disc and the blade roots 24. In operation, the seal 70 opens and, by reaction mechanical support radial against the outer frustoconical wall of the groove 68 of the intermediate ring 66, plate the seal 70 axially against the teeth 20 of the disc and the blade roots 24. The seal 70 therefore relies both annularly on the one hand against the intermediate ring 66 and 25 on the other hand against the teeth 20 of the disk and the blade roots 24, and thus ensures the seal between these two parts. The seal 70 can therefore perform the same role and has the same efficiency in the groove 68, that the arm 56 of the labyrinth ring is bent or not. In addition, the intermediate arm / ring seal, intermediate ring / seal and seal / disc teeth and blade roots is ensured in all operating conditions.
    [0010] As for the prior art, an upstream and anterior annular hook 72 may be formed on the upstream radial wall 38 of the platform, around a radial flange 72 formed at the end of the arm 56 of the labyrinth ring 52. This hook prevents the arm 56 from too much to deviate axially upstream during its deflection in rotation.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Rotary assembly for a turbomachine, comprising: a disc (16) having an outer periphery having an alternation of cells (22) and teeth (20) extending from upstream to downstream of the disc, vanes (14) extending radially from the disk (16) and whose feet (24) are engaged axially in the cells (22) and retained radially by the teeth of the disk, upstream and / or downstream of the disk, an annular sealing flange (52) cavities (36) formed radially between respectively the blade roots and the bottoms of the disk cells, said flange comprising an inner portion (58) retained by the disk, and an outer portion (56) arranged axially facing the upstream and / or downstream ends, respectively, of the disc teeth and blade roots, characterized in that it further comprises an intermediate ring (66) which is arranged axially between the flange (52) and the teeth (20). ) of the disc, and radially between the inner part and the outer part of the disc, and in that it also comprises a seal (70) which is arranged axially between, on one side, the intermediate ring (66) and, on the other hand, the teeth (20). of the disc and the blade roots (24), the intermediate ring and the seal being configured to rotate the seal between, on one side, the sealing flange (52) and, on the other hand, the teeth of the disc and the feet of blades.
    [0002]
    2. Rotary assembly according to claim 1, characterized in that the intermediate ring (66) and the seal (70) are split and open radially in rotation.
    [0003]
    3. Rotary assembly according to one of claims 1 or 2, characterized in that the sealing flange (52) has an inner frustoconical surface (64) inclined axially towards the disk and radially outwardly, and arranged facing axial and radial of the intermediate ring (66).
    [0004]
    4. Rotary assembly according to claim 3, characterized in that the intermediate ring (66) has an outer frustoconical surface axially inclined towards the disk and radially outwardly, and complementary to the frustoconical surface (64) of the flange of sealing (52).
    [0005]
    5. Rotary assembly according to one of the preceding claims, characterized in that the intermediate ring (66) comprises an inner frustoconical surface axially inclined towards the disk and radially outwardly, and arranged radially facing the seal (70).
    [0006]
    6. Rotary assembly according to one of the preceding claims, characterized in that the seal (70) is arranged in an annular groove (68) downstream of the intermediate ring (66).
    [0007]
    7. Rotary assembly according to one of the preceding claims, characterized in that the seal (70) has a diameter of between 0.6 and 1.2 mm.
    [0008]
    8. Rotary assembly according to one of the preceding claims, characterized in that the intermediate ring (66) and the seal (70) are arranged integrally externally to the cavities funds cell (36).
    [0009]
    Turbomachine turbine, characterized in that it comprises a rotary assembly according to one of the preceding claims.
    [0010]
    10. Turbomachine, such as a turbojet or turboprop, characterized in that it comprises a rotary assembly according to one of claims 1 to 8.
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    RU2016150099A|2018-07-26|
    US20170218781A1|2017-08-03|
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    CN106460522A|2017-02-22|
    RU2695545C2|2019-07-25|
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    BR112016030417A8|2021-06-29|
    JP6630295B2|2020-01-15|
    JP2017528634A|2017-09-28|
    US10385706B2|2019-08-20|
    FR3022944B1|2020-02-14|
    WO2015197980A1|2015-12-30|
    BR112016030417A2|2017-08-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20120171022A1|2011-01-04|2012-07-05|General Electric Company|Systems, methods, and apparatus for a turbine interstage rim seal|
    FR2973433A1|2011-04-04|2012-10-05|Snecma|Turbine rotor for low pressure turbomachine e.g. turbojet of aircraft, has upstream and downstream disks arranged coaxially, and bearing unit supporting end portion of flange to prevent deviation of flange of downstream disk|FR3086328A1|2018-09-20|2020-03-27|Safran Aircraft Engines|TURBINE WITH BLADES HELD AXIALLY, FOR TURBOMACHINE|
    FR3108361A1|2020-03-19|2021-09-24|Safran Aircraft Engines|TURBINE WHEEL FOR AN AIRCRAFT TURBOMACHINE|US2851246A|1956-10-24|1958-09-09|United Aircraft Corp|Turbine or compressor construction and method of assembly|
    GB1460714A|1973-06-26|1977-01-06|Rolls Royce|Bladed rotor for a gas turbine engine|
    GB2042652B|1979-02-21|1983-07-20|Rolls Royce|Joint making packing|
    GB2081392B|1980-08-06|1983-09-21|Rolls Royce|Turbomachine seal|
    GB2097480B|1981-04-29|1984-06-06|Rolls Royce|Rotor blade fixing in circumferential slot|
    US4580946A|1984-11-26|1986-04-08|General Electric Company|Fan blade platform seal|
    FR2639402B1|1988-11-23|1990-12-28|Snecma|TURBOMACHINE ROTOR WING DISC|
    US5158305A|1992-01-31|1992-10-27|Eg&G Pressure Science, Inc.|Pressure-energized two-element seal|
    US5257909A|1992-08-17|1993-11-02|General Electric Company|Dovetail sealing device for axial dovetail rotor blades|
    US6464453B2|2000-12-04|2002-10-15|General Electric Company|Turbine interstage sealing ring|
    US6884028B2|2002-09-30|2005-04-26|General Electric Company|Turbomachinery blade retention system|
    FR2867223B1|2004-03-03|2006-07-28|Snecma Moteurs|TURBOMACHINE AS FOR EXAMPLE A TURBOJET AIRCRAFT|
    US7217089B2|2005-01-14|2007-05-15|Pratt & Whitney Canada Corp.|Gas turbine engine shroud sealing arrangement|
    US7549841B1|2005-09-03|2009-06-23|Florida Turbine Technologies, Inc.|Pressure balanced centrifugal tip seal|
    US8105041B2|2005-09-07|2012-01-31|Siemens Aktiengesellschaft|Arrangement for axially securing rotating blades in a rotor, sealing element for such an arrangement, and use of such an arrangement|
    FR2899274B1|2006-03-30|2012-08-17|Snecma|DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE|
    US7470113B2|2006-06-22|2008-12-30|United Technologies Corporation|Split knife edge seals|
    JP5056152B2|2007-05-15|2012-10-24|株式会社島津製作所|Turbo molecular pump|
    US8388309B2|2008-09-25|2013-03-05|Siemens Energy, Inc.|Gas turbine sealing apparatus|
    US8376697B2|2008-09-25|2013-02-19|Siemens Energy, Inc.|Gas turbine sealing apparatus|
    US8079807B2|2010-01-29|2011-12-20|General Electric Company|Mounting apparatus for low-ductility turbine shroud|
    FR2982635B1|2011-11-15|2013-11-15|Snecma|AUBES WHEEL FOR A TURBOMACHINE|
    FR3011031B1|2013-09-25|2017-12-29|Herakles|ROTARY ASSEMBLY FOR TURBOMACHINE|
    FR3011032B1|2013-09-25|2017-12-29|Snecma|ROTARY ASSEMBLY FOR TURBOMACHINE|
    FR3024883B1|2014-08-14|2016-08-05|Snecma|TURBOMACHINE MODULE|
    US20170350265A1|2016-06-01|2017-12-07|United Technologies Corporation|Flow metering and directing ring seal|FR3065483B1|2017-04-24|2020-08-07|Safran Aircraft Engines|SEALING DEVICE BETWEEN ROTOR AND TURBOMACHINE STATOR|
    CN112594068B|2021-01-21|2021-05-28|中国航发上海商用航空发动机制造有限责任公司|Disc drum sealing mechanism of aircraft engine and aircraft engine|
    法律状态:
    2015-06-18| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-01| PLSC| Publication of the preliminary search report|Effective date: 20160101 |
    2016-06-06| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 5 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1455997A|FR3022944B1|2014-06-26|2014-06-26|ROTARY ASSEMBLY FOR TURBOMACHINE|
    FR1455997|2014-06-26|FR1455997A| FR3022944B1|2014-06-26|2014-06-26|ROTARY ASSEMBLY FOR TURBOMACHINE|
    US15/320,378| US10385706B2|2014-06-26|2015-06-24|Rotary assembly for a turbomachine|
    BR112016030417A| BR112016030417A8|2014-06-26|2015-06-24|swivel assembly for a turbomachine, turbine for a turbomachine and turbomachine|
    PCT/FR2015/051699| WO2015197980A1|2014-06-26|2015-06-24|Rotary assembly for turbomachine|
    CA2952752A| CA2952752A1|2014-06-26|2015-06-24|Rotary assembly for turbomachine|
    EP15745523.9A| EP3161263B1|2014-06-26|2015-06-24|Drehbare vorrichtung einer turbomaschine|
    CN201580034455.8A| CN106460522B|2014-06-26|2015-06-24|The rotary components of turbine and the turbine of turbine and turbine|
    JP2016575146A| JP6630295B2|2014-06-26|2015-06-24|Rotor assembly for turbomachinery|
    RU2016150099A| RU2695545C2|2014-06-26|2015-06-24|Rotor device for turbomachine , turbine for turbomachine and turbomachine|
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