• 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:
    A turbine ring assembly includes a plurality of ring sectors (10) of ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3) integral with a turbine casing (30) and having two annular flanges (32, 54), each ring sector (10) having two tabs (14, 16) held between the two annular flanges (32, 36) of the ring support structure ( 3). The ring support structure includes an annular retention flange mounted on the turbine housing, the annular retaining flange having an annular web forming one (36) of the flanges of the ring support structure. The two annular flanges (32, 54) of the ring support structure (3) exert stress on the tabs (14, 16) of the ring sectors (10). One (54) of the flanges of the ring support structure (3) is elastically deformable in the axial direction (DA) of the turbine ring (1).
    公开号:FR3036433A1
    申请号:FR1554605
    申请日:2015-05-22
    公开日:2016-11-25
    发明作者:Lucien Henri Jacques Quennehen；Sebastien Serge Francis Congratel
    申请人:SNECMA SAS；Herakles SA；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to a turbine ring assembly for a turbomachine, which assembly comprises a plurality of one-piece ring segments of ceramic matrix composite material and a support structure of 'ring. The field of application of the invention is in particular that of aeronautical gas turbine engines. The invention is however applicable to other turbomachines, for example industrial turbines.
    [0002] Ceramic matrix composite materials, or CMCs, are known for their good mechanical properties that make them suitable for constituting structural elements, and for their ability to retain these properties at high temperatures. In aviation gas turbine engines, improved efficiency and reduced pollutant emissions lead to the search for operation at ever higher temperatures. In the case of all-metal turbine ring assemblies, it is necessary to cool all the elements of the assembly and in particular the turbine ring which is subjected to high temperature flows. This cooling has a significant impact on the engine performance since the cooling flow used is taken from the main flow of the engine. In addition, the use of metal for the turbine ring limits the possibilities of increasing the temperature at the turbine, which would nevertheless make it possible to improve the performance of the aeronautical engines. The use of CMC for various hot parts of such engines has already been considered, especially since CMCs have a lower density than refractory metals traditionally used.
    [0003] Thus, the realization of one-piece CMC turbine ring sectors is described in particular in US 2012/0027572. The ring sectors comprise an annular base whose internal face defines the inner face of the turbine ring and an outer face from which two leg portions extend, the ends of which are engaged in housings of a ring support metal structure.
    [0004] 3036433 2 The use of ring segments in CMC significantly reduces the ventilation needed to cool the turbine ring. However, the seal between the gaseous flow vein on the inner side of the ring sectors and the outer side of the ring sectors remains a problem. Indeed, in order to ensure a good seal, it must be possible to ensure good contact between the legs of the CMC ring sectors and the metal flanges of the ring support structure. However, the differential expansions between the metal of the ring support structure and the CMC of the ring sectors complicates the maintenance of the seal between these elements. Thus, during differential expansions and depending on the mounting geometry of the ring sectors on the ring support structure, the flanges of the ring support structure may no longer be in contact with the legs of the sectors or, at On the contrary, exert too much stress on the legs of the sectors, which can damage them. Furthermore, as described in US 2012/0027572, the maintenance of the ring sectors on the ring support structure requires the use of a U-section clamp, which complicates the assembly of the sectors and increases the cost of the whole.
    [0005] OBJECT AND SUMMARY OF THE INVENTION The object of the invention is to avoid such drawbacks and proposes for this purpose a turbine ring assembly comprising a plurality of ceramic matrix composite ring sectors forming a turbine ring and a ring support structure secured to a turbine casing and having two annular flanges, each ring sector having an annular base portion with an inner face defining the inner face of the turbine ring and an outer face to from which two tabs radially extend, the tabs of each ring sector being held between the two annular flanges of the ring support structure, characterized in that the ring support structure comprises a ring flange on the turbine housing, the annular retaining flange having an annular web forming one of the flanges of the ring support structure and that the their annular flanges of the ring support structure exert stress on the legs of the ring sectors, at least one of the flanges of the ring support structure being elastically deformable in the axial direction of the ring ring. turbine. Due to the presence of at least one elastically deformable flange, the contact between the flanges of the ring support structure 5 and the tabs of the ring sectors can be maintained independently of temperature variations. Indeed, the ring sectors can be mounted between the flanges with a "cold" prestressing, so that the contact between the ring sectors and the flanges is assured regardless of the temperature conditions. The flexibility of at least one of the flanges of the ring support structure allows its deformation to accommodate the differential thermal expansions between the ring sectors and the flanges so as to avoid exerting too much stress on the ring support structure. the ring areas. According to a first aspect of the turbine ring assembly 15 according to the invention, the flange comprises a first series of teeth distributed circumferentially on said flange while the turbine casing comprises a second series of teeth distributed circumferentially. on said housing, the teeth of the first set of teeth and the teeth of the second set of teeth forming a circumferential clutch. This connection by interconnection allows easy assembly and disassembly of ring sectors. According to a second aspect of the turbine ring assembly according to the invention, the turbine casing comprises an annular boss extending between a shell of the casing and the flange of the ring structure. This prevents upstream-downstream leakage between the housing and the flange. According to a third aspect of the turbine ring assembly according to the invention, at least one of the annular flanges of the ring support structure has a lip on its face facing the tabs of the ring sectors. The presence of a lip on a flange facilitates the definition of the contact portion between the flange of the ring support structure and the tabs of the ring sectors facing it. According to a fourth aspect of the turbine ring assembly 35 according to the invention, it further comprises a first plurality of pins engaged both in one of the annular flanges of the ring support structure and the tabs of the ring sectors facing said annular flange, and a second plurality of pins engaged both in the other annular flange of the ring support structure and the tabs of the ring sectors opposite said other annular flange. The pins make it possible to block the possible rotation of the ring sectors in the ring support structure and to hold them radially in said structure. According to a fifth aspect of the turbine ring assembly according to the invention, each elastically deformable flange of the ring support structure has a thickness less than that of the other flange of said ring support structure. The present invention also relates to a method of making a turbine ring assembly comprising: - manufacturing a plurality of ceramic matrix composite material ring sectors, each ring sector having a portion forming an annular base with an inner face defining the inner face of a turbine ring and an outer face from which radially extend first and second legs, - producing a ring support structure comprising a first annular flange secured to a turbine casing and an annular retaining flange having a second annular flange, said flange being intended to be assembled with the turbine casing, - mounting each first leg of the ring sectors on the first annular flange of the ring support structure, 25 - the assembly by interconnection of the annular retention flange on the turbine casing, the second flange being held in abutment on each second leg, said annular retention flange being mounted axially on the turbine casing, at least one of the flanges of the ring-supporting structure being elastically deformable in the axial direction of the ring of turbine. Thanks to the assembly by interconnection of the flange, it is possible to position the legs of the ring sectors between the flanges of the ring support structure without having to force on said tabs which are then held with a stress between the flanges after 35 mounting of the flange.
    [0006] According to a first aspect of the method of producing a turbine ring assembly according to the invention, the turbine casing comprises an annular boss extending between a shell of said casing and the flange of the ring structure.
    [0007] According to a second aspect of the method for producing a turbine ring assembly according to the invention, at least one of the annular flanges of the ring support structure comprises a lip on its face opposite the legs of the sectors of the ring. 'ring. According to a third aspect of the method of producing a turbine ring assembly according to the invention, it further comprises engaging a first plurality of pins in both the first annular flange of the structure. of ring support and the first tabs of the ring sectors during assembly of said first tabs and, after assembly by interconnection of the annular retention flange, the engagement of a second plurality of pins in both the second flange ring and the second legs of the ring sectors. According to a fourth aspect of the method of producing a set of turbine rings according to the invention, the elastically deformable flange of the ring support structure has a thickness less than that of the other flange of said structure of the ring structure. ring support. Brief description of the drawings. The invention will be better understood on reading the following, by way of indication but not limitation, with reference to the accompanying drawings in which: - Figure 1 is a radial half-sectional view showing an embodiment of a turbine ring assembly according to the invention; Figures 2 to 6 show schematically the mounting of a ring sector in the ring support structure of the ring assembly of Figure 1; - Figure 7 is a schematic perspective view of the flange of Figures 1, 3, 4 and 5.
    [0008] DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 of ceramic matrix composite material (CMC) and a metal ring support structure 3. turbine ring 1 surrounds a set of rotary blades 5. The turbine ring 1 is formed of a plurality of ring sectors 10, Figure 1 being a radial sectional view along a plane passing between two sectors of rings contiguous. The arrow DA indicates the axial direction with respect to the turbine ring 1 while the arrow DR indicates the radial direction with respect to the turbine ring 1. Each ring sector 10 has a substantially Tu-shaped section. inverted with an annular base 12 whose inner face coated with a layer 13 of abradable material and / or a thermal barrier defines the stream of flow of gas in the turbine.
    [0009] Upstream and downstream tabs 14, 16 extend from the outer face of the annular base 12 in the radial direction DR. The terms "upstream" and "downstream" are used herein with reference to the flow direction of the gas flow in the turbine (arrow F). The ring support structure 3 is formed of two parts, namely a first part corresponding to an annular upstream radial flange 32 which is preferably formed integrally with a turbine casing 30 and a second part corresponding to an annular retention flange 50 mounted on the turbine casing 30. The annular upstream radial flange 32 comprises a lip 34 on its face opposite the upstream lugs 14 of the ring sectors 10, the lip 34 being supported on the outer face 14a of the upstream lugs 14 On the downstream side, the flange 50 comprises an annular web 57 which forms an annular downstream radial flange 54 having a lip 55 on its opposite side of the downstream tabs 16 of the ring sectors 10, the lip 55 being supported on the face 16. The flange 50 comprises an annular body 51 extending axially and comprising, on the upstream side, the annular web 57 and, on the downstream side, a first series of teeth 52 distributed from one side to the other. circumferentially on the flange 50 and spaced from each other by first engagement passages 53 (Figures 4 and 7). The turbine casing 30 has on the downstream side a second series of teeth 35 extending radially from the inner surface of the ferrule 38 of the turbine casing 30. The teeth 35 are distributed circumferentially on the inner surface 38a of the turbine housing 30. ferrule 38 and spaced apart from each other by second engagement passages 36 (Figure 4). The teeth 52 and 35 cooperate with each other to form a circumferential clutch.
    [0010] As will be explained in detail below, the tabs 14 and 16 of each ring sector 10 are preloaded between the annular flanges 32 and 54 so that the flanges exert, at least "cold", that is to say at an ambient temperature of about 20 ° C, but also at all operating temperatures of the turbine, a stress on the lugs 14 and 16 and thus a tightening of the sectors by the flanges. This constraint is maintained at all temperatures at which the ring assembly can be subjected during operation of the turbine and is controlled, that is to say without over-constraining the ring sectors, thanks to the presence of at least one elastically deformable flange as explained above. Furthermore, in the example described here, the ring sectors 10 are further maintained by blocking pins. More precisely, and as illustrated in FIG. 1, pins 40 are engaged both in the annular upstream radial flange 32 of the ring support structure 3 and in the upstream lugs 14 of the ring sectors 10. At this point, FIG. Indeed, the pins 40 each pass respectively through an orifice 33 formed in the annular upstream radial flange 32 and an orifice 15 formed in each upstream lug 14, the orifices 33 and 15 being aligned during the assembly of the ring sectors 10 on the structure of FIG. Similarly, studs 41 are engaged both in the annular downstream radial flange 54 of the flange 50 and in the downstream lugs 16 of the ring sectors 10. For this purpose, the pins 41 pass through each respectively an orifice 56 formed in the annular downstream radial flange 54 and an orifice 17 formed each downstream lug 16, the orifices 56 and 17 being aligned during assembly of the ring sectors 10 on the ring support structure 3. According to a variant of re alisation, pins having a length greater than or equal to the distance between the two flanges can be used. In this case, each peg passes through the orifices present on the two flanges of the ring structure and on the two lugs of the ring sectors.
    [0011] In addition, inter-sector sealing is provided by sealing tabs housed in facing grooves in the facing edges of two adjacent ring sectors. A tongue 22a extends over almost the entire length of the annular base 12 in the middle portion thereof. Another tab 22b extends along the tab 14 and a portion of the annular base 12. Another tab 22c extends along the tab 16. At one end, the tab 22c abuts the tab. tongue 22a and on the tongue 22b. The tongues 22a, 22b, 22c are for example metallic and are mounted with cold play in their housings to ensure the sealing function at the temperatures encountered in service.
    [0012] The gap-free assembly of the tabs 14, 16 of the CMC ring sector with metal parts of the ring support structure is made possible despite the difference in coefficient of thermal expansion because: is made at a distance from the hot face of the annular base 12 exposed to the gaseous flow, - the lugs 14, 16 advantageously have in radial section a relatively large length relative to their average thickness so that an effective thermal decoupling is obtained between the annular base 12 and the ends of the tabs 14, 16, and 20 - one of the flanges of the ring structure is elastically deformable, which makes it possible to compensate for the differential expansions between the tabs of the CMC ring sectors and the flanges of the metal ring support structure without significantly increasing the stress exerted "cold" by the flanges on the legs of the ring sectors. Conventionally, ventilation orifices 32a formed in the flange 32 make it possible to bring cooling air to the outside of the turbine ring 10. In addition, the seal between the upstream and the downstream of the the turbine ring assembly 30 is provided by an annular boss 31 extending radially from the inner surface 38a of the shell 38 of the turbine casing 3 and the free end of which is in contact with the surface of the body 51 of the Flange 50. A method of producing a set of turbine rings corresponding to that shown in FIG. 1 is now described.
    [0013] Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by forming a fibrous preform having a shape close to that of the ring sector and densifying the ring sector by a ceramic matrix.
    [0014] For producing the fiber preform, ceramic fiber yarns, for example SiC fiber yarns such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon", or carbon fiber yarns, may be used. The fiber preform is advantageously made by three-dimensional weaving, or multi-layer weaving with provision of debonding zones to separate the parts of preforms corresponding to the tabs 14 and 16 of the sectors 10. The weaving may be of the interlock type, as illustrated. Other three-dimensional weave or multilayer weaves may be used such as multi-web or multi-satin weaves. Reference can be made to WO 2006/136755. After weaving, the blank may be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification being achieved in particular by chemical vapor infiltration (CVI) or MI process. ("Melt Infiltrated", liquid silicon introduced into the fibrous preform by capillarity, the preform being previously consolidated by a CVI phase) which are well known per se. A detailed example of manufacture of CMC ring sectors is described in US 2012/0027572. The ring support structure 3 is made of a metallic material such as Inconel, the C263 superalloy or Waspaloy®. The embodiment of the turbine ring assembly is continued by mounting the ring sectors 10 on the ring support structure 30. As shown in FIGS. 2 and 4, the ring sectors 10 are first fixed by their upstream leg 14 to the annular upstream radial flange 32 of the ring support structure 3 by pins 40 which are engaged in the aligned orifices 33 and 15 formed respectively in the annular upstream radial flange 32 and in the upstream leg 14.
    [0015] Once all the ring sectors 10 thus fixed to the annular upstream radial flange 32, the annular retaining flange 50 is assembled by interconnection between the turbine casing 3 and the downstream lugs of the sectors 30. According to the embodiment described here, the gap E between the annular upstream radial flange 54 formed by the annular web 57 of the flange 50 and the outer surface 52a of the teeth 52 of said flange is less than the distance D present between the outer face 16a of the downstream lugs 16 of the ring sectors and the inner face 35b of the teeth 35 present on the turbine casing 30. In the example described here, the distance E is measured between the lip 55 present in the end of the annular flange 54 and the outer surface 52a of the teeth 52.
    [0016] In the embodiments of the turbine ring assembly of the invention in which the annular flange (s) have no lips, the gap is measured between the inner face of the flange on the flange which will be in contact with the outer surface of the downstream legs of the ring sectors and the outer surface of the teeth of the flange.
    [0017] By defining a gap E between the annular upstream radial flange and the outer surface of the teeth of the lower flange at the distance D between the external face of the downstream lugs of the ring sectors and the internal face of the teeth present on the turbine casing, it is possible to mount the ring segments prestressed between the flanges of the ring support structure. However, in order not to damage the tabs of the CMC ring sectors during assembly and in accordance with the invention, the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction DA of the invention. 'ring. In the example described here, it is the annular downstream radial flange 54 25 on the flange 50 which is elastically deformable. Indeed, the annular web 57 forming the annular downstream radial flange 54 of the ring support structure 3 has a small thickness, for example less than 2.5 mm, which gives it a certain elasticity. As illustrated in FIGS. 5 and 6, the flange 50 is mounted on the turbine casing 30 by placing the teeth 52 present on the flange 50 opposite the engagement passages 36 formed on the turbine casing 30. , the teeth 35 present on said turbine housing being also placed opposite the engagement passages 53 formed between the teeth 52 on the flange 50. The gap E being smaller than the distance D, it is necessary to apply an axial force FA to the flange 50 in the direction indicated in Figure 6 to engage the teeth 52 au- 3036433 11 beyond the teeth 35 and allow a rotation R of the flange at an angle corresponding substantially to the width of the teeth 35 and 52. After this rotation, the flange 50 is released, the latter then being maintained in axial stress between the upstream lugs 16 of the ring sectors 10 and the inner surface 35b of the teeth 35 of the turbine casing 30. A times the flask so put in place, pins 41 are engaged in the aligned orifices 56 and 17 respectively formed in the annular downstream radial flange 54 and in the downstream lug 16. Each lug 14 or 16 of the ring sector may comprise one or more openings for the 10 passage of a blocking pin.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbine ring assembly comprising a plurality of ring sectors (10) of ceramic matrix composite material 5 forming a turbine ring (1) and a ring support structure (3) integral with a turbine casing (30) and having two annular flanges (32, 54), each ring sector (10) having an annular base portion (12) with an inner face defining the inner face of the turbine ring (1) and a outer face from which radially extend two tabs (14, 16), the tabs (14, 16) of each ring sector (10) being held between the two annular flanges (32, 36) of the structure ring support means (3), characterized in that the ring support structure comprises an annular retention flange mounted on the turbine casing, the annular retaining flange having an annular web forming one of the flanges of the structure ring support and that the two annular flanges (32, 54) of the ring the ring support structure (3) exert stress on the legs (14, 16) of the ring sectors (10), at least one (54) of the flanges of the ring support structure (3) being elastically deformable in the axial direction (DA) of the turbine ring (1).
    [0002]
    2. An assembly according to claim 1, characterized in that the flange comprises a first series of teeth distributed circumferentially on said flange while the turbine casing comprises a second series of teeth distributed circumferentially on said casing and in that that the teeth of the first set of teeth and the teeth of the second set of teeth form a circumferential clutch. 30
    [0003]
    3. An assembly according to claim 1 or 2, characterized in that the turbine housing comprises an annular boss extending between a shell of said housing and the flange of the ring structure.
    [0004]
    A turbine ring assembly according to any one of claims 1 to 3, characterized in that at least one of the annular flanges (32; 54) of the ring support structure comprises a lip ( 34; 55) on its face opposite the tabs (14; 16) of the ring sectors (10).
    [0005]
    Turbine ring assembly according to any one of claims 1 to 4, characterized in that it further comprises a first plurality of pins (40) engaged both in one of the annular flanges (32) of the ring support structure (3) and the tabs (14) of the ring sectors (10) facing said annular flange (32) and a second plurality of pins (41) engaged both in the other flange annular (54) of the ring support structure (3) and the tabs (16) of the ring sectors (10) facing said other annular flange (54).
    [0006]
    Turbine ring assembly according to any one of claims 1 to 5, characterized in that each elastically deformable flange (54) of the ring support structure (3) has a thickness less than that of the another flange (32) of said ring support structure (3).
    [0007]
    7. A method of producing a set of turbine rings 20 comprising: - manufacturing a plurality of ring sectors (10) of ceramic matrix composite material, each ring sector (10) having a portion Annular base (12) with an inner face defining the inner face of a turbine ring (1) and an outer face 25 from which radially extend first and second legs (14, 16), - the manufacture a ring support structure (3) comprising a first annular flange (32) integral with a turbine casing and an annular retaining flange having a second annular flange (54), said flange being intended to be assembled with the turbine casing, - the mounting of each first tab (14) of the ring sectors (10) on the first annular flange of the ring support structure, - the mounting by clutch of the annular retention flange on the turbine housing, the second brid e (54) being held in abutment 3036433 14 on each second lug (16), said annular retention flange being mounted in axial prestress on the turbine casing, at least one (54) of the flanges of the ring support structure (3) being elastically deformable in the axial direction (DA) of the turbine ring (1). 5
    [0008]
    8. Method according to claim 7, characterized in that the turbine casing comprises an annular boss extending between a shell of said housing and the flange of the ring structure. 10
    [0009]
    9. A method according to claim 7 or 8, characterized in that at least one of the annular flanges (32; 54) of the ring support structure (3) has a lip (34; 55) on its opposite side. tabs (14; 16) of the ring sectors (10). 15
    [0010]
    The method according to any one of claims 7 to 9, characterized in that it further comprises engaging a first plurality of pins (40) at a time in the first annular flange (32) of the structure ring support (3) and the first tabs (14) of the ring sectors (10) during assembly of said first tabs and, after assembly by interconnection of the annular retention flange, the engagement of a second plurality of pins (41) in both the second annular flange (54) and the second legs (16) of the ring sectors (10).
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3036433B1|2019-09-13|TURBINE RING ASSEMBLY WITH CRABOT HOLDING
    EP3298244B1|2020-11-11|Turbine ring assembly with axial retention
    EP3390782B1|2019-11-27|Turbine ring assembly, elastically retained in a cold-state
    EP3390783B1|2019-10-02|Turbine shroud assembly and corresponding turbine
    EP2406466B1|2012-11-07|Turbine ring assembly
    FR3036435A1|2016-11-25|TURBINE RING ASSEMBLY
    EP3271556B1|2021-07-07|Assembly of turbine rings comprising shrouds made of ceramic composite
    EP3433471B1|2020-01-29|Turbine shroud seal assembly with specific support in cold conditions
    CA2986663A1|2016-12-01|Turbine ring assembly supported by flanges
    FR3033825A1|2016-09-23|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL
    EP3274565B1|2021-09-22|Turbine ring assembly with specific holding device for ceramic matrix composite ring segments
    FR3055146A1|2018-02-23|TURBINE RING ASSEMBLY
    FR3056637A1|2018-03-30|TURBINE RING ASSEMBLY WITH COLD SETTING
    WO2018172655A1|2018-09-27|Turbine ring assembly
    FR2942844A1|2010-09-10|High pressure turbine shroud assembly for e.g. aeronautical gas turbine engine, has ring sector axially maintained by mutual engagement of groove and rib on supporting surfaces opposite to anchoring tab and flange of support structure
    WO2017194860A1|2017-11-16|Turbine ring assembly with cold setting
    FR3041994A1|2017-04-07|TURBINE RING ASSEMBLY
    FR2942845A1|2010-09-10|High pressure turbine ring assembly for gas turbine of aviation engine, has ring sectors with pie shaped section, and upstream and downstream end portions of tabs maintained without radial clearance by metallic ring support structure
    同族专利:
    公开号 | 公开日
    FR3036433B1|2019-09-13|
    US10858958B2|2020-12-08|
    CN107810310A|2018-03-16|
    US20180142572A1|2018-05-24|
    WO2016189222A1|2016-12-01|
    CN107810310B|2021-01-08|
    EP3298245A1|2018-03-28|
    EP3298245B1|2019-07-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4087199A|1976-11-22|1978-05-02|General Electric Company|Ceramic turbine shroud assembly|
    GB2485016A|2010-10-29|2012-05-02|Gen Electric|Turbine component with resilient mounting|
    EP2631434A2|2012-02-22|2013-08-28|General Electric Company|Low-ductility turbine shroud|EP3473806A1|2017-10-23|2019-04-24|Safran Aircraft Engines|Turbine engine casing comprising a central portion projecting relative to two side portions in a joining region|
    CN110506149A|2017-03-16|2019-11-26|赛峰航空器发动机|Turbine ring assemblies|
    EP3613950A1|2018-08-22|2020-02-26|United Technologies Corporation|Blade outer air seal formed of laminate and having radial support hooks|
    FR3093541A1|2019-03-08|2020-09-11|Safran Aircraft Engines|Double Rotor Aircraft Gas Turbine|US5281090A|1990-04-03|1994-01-25|General Electric Co.|Thermally-tuned rotary labyrinth seal with active seal clearance control|
    US5632600A|1995-12-22|1997-05-27|General Electric Company|Reinforced rotor disk assembly|
    FR2800797B1|1999-11-10|2001-12-07|Snecma|ASSEMBLY OF A RING BORDING A TURBINE TO THE TURBINE STRUCTURE|
    FR2867229B1|2004-03-05|2006-07-28|Snecma Moteurs|TURBOMACHINE BEARING BEARING WITH REDUCED SIZE|
    JP4822716B2|2005-02-07|2011-11-24|三菱重工業株式会社|Gas turbine with seal structure|
    FR2887601B1|2005-06-24|2007-10-05|Snecma Moteurs Sa|MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART|
    FR2930592B1|2008-04-24|2010-04-30|Snecma|TURBINE DISPENSER FOR A TURBOMACHINE|
    ES2398727T3|2009-03-09|2013-03-21|Snecma|Turbine ring set|
    RU2547542C2|2010-11-29|2015-04-10|Альстом Текнолоджи Лтд|Axial gas turbine|
    US9188062B2|2012-08-30|2015-11-17|Mitsubishi Hitachi Power Systems, Ltd.|Gas turbine|FR3033825B1|2015-03-16|2018-09-07|Safran Aircraft Engines|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|
    FR3049003B1|2016-03-21|2018-04-06|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITHOUT COLD MOUNTING SET|
    FR3056637B1|2016-09-27|2018-10-19|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITH COLD SETTING|
    EP3299591B1|2016-09-27|2019-12-18|Siemens Aktiengesellschaft|Guide blade carrier, turbine casing and turbine|
    CN109339955B|2018-12-16|2021-09-03|中国航发沈阳发动机研究所|Supporting structure of deflation valve adjusting mechanism|
    US10815810B2|2019-01-10|2020-10-27|Raytheon Technologies Corporation|BOAS assemblies with axial support pins|
    FR3093938B1|2019-03-19|2021-02-26|Safran Ceram|Support tools for porous preforms to be infiltrated and oven using such tools|
    US11255210B1|2020-10-28|2022-02-22|Rolls-Royce Corporation|Ceramic matrix composite turbine shroud assembly with joined cover plate|
    法律状态:
    2016-05-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-25| PLSC| Publication of the preliminary search report|Effective date: 20161125 |
    2017-04-13| PLFP| Fee payment|Year of fee payment: 3 |
    2017-08-25| CD| Change of name or company name|Owner name: HERAKLES, FR Effective date: 20170725 Owner name: SNECMA, FR Effective date: 20170725 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 Owner name: SAFRAN CERAMICS, FR Effective date: 20170719 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 4 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 6 |
    2022-02-11| ST| Notification of lapse|Effective date: 20220105 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1554605A|FR3036433B1|2015-05-22|2015-05-22|TURBINE RING ASSEMBLY WITH CRABOT HOLDING|
    FR1554605|2015-05-22|FR1554605A| FR3036433B1|2015-05-22|2015-05-22|TURBINE RING ASSEMBLY WITH CRABOT HOLDING|
    CN201680030536.5A| CN107810310B|2015-05-22|2016-05-18|Claw clutch retained turbine ring assembly|
    US15/575,137| US10858958B2|2015-05-22|2016-05-18|Turbine ring assembly held by jaw coupling|
    PCT/FR2016/051167| WO2016189222A1|2015-05-22|2016-05-18|Turbine ring assembly retained in the manner of a dog clutch|
    EP16726368.0A| EP3298245B1|2015-05-22|2016-05-18|Turbine ring assembly retained in the manner of a dog clutch|
    [返回顶部]