WO2011107708A1 - Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication - Google Patents
Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication Download PDFInfo
- Publication number
- WO2011107708A1 WO2011107708A1 PCT/FR2011/050428 FR2011050428W WO2011107708A1 WO 2011107708 A1 WO2011107708 A1 WO 2011107708A1 FR 2011050428 W FR2011050428 W FR 2011050428W WO 2011107708 A1 WO2011107708 A1 WO 2011107708A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- band
- leg
- tabs
- preform
- legs
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/14—Making preforms characterised by structure or composition
- B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
-
- D—TEXTILES; PAPER
- D03—WEAVING
- D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
- D03D11/00—Double or multi-ply fabrics not otherwise provided for
- D03D11/02—Fabrics formed with pockets, tubes, loops, folds, tucks or flaps
-
- D—TEXTILES; PAPER
- D03—WEAVING
- D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
- D03D23/00—General weaving methods not special to the production of any particular woven fabric or the use of any particular loom; Weaves not provided for in any other single group
-
- D—TEXTILES; PAPER
- D03—WEAVING
- D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
- D03D25/00—Woven fabrics not otherwise provided for
- D03D25/005—Three-dimensional woven fabrics
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/748—Machines or parts thereof not otherwise provided for
- B29L2031/7504—Turbines
-
- D—TEXTILES; PAPER
- D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B2505/00—Industrial
- D10B2505/02—Reinforcing materials; Prepregs
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
Definitions
- the field of application of the invention is in particular that of aeronautical gas turbine engines.
- the invention is however applicable to other types of turbomachines, for example industrial turbines.
- CMCs Metal 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.
- Fig. 1 shows a high pressure turbine ring assembly having a CMC turbine ring 10 and a ring support metal structure 13.
- the turbine ring 10 surrounds a set of rotating blades 15.
- the dawn of turbine 10 is formed of a plurality of sectors of rings 100, Figure 1 being a meridian sectional view along a plane passing between two contiguous rings.
- Each ring sector 100 has a substantially inverted ⁇ (pi) section with a ring-shaped base 112 and whose inner face coated with a layer 113 of abradable material defines the flow path of the ring. gaseous flow of the turbine.
- Tabs 114, 116 extend from the outer face of the base 112.
- One of the tabs, or upstream tab 114 has a meridian section substantially L-shaped lying and extends upstream and defines with the end upstream of the base 112 a U-shaped portion defining a housing 115 extending over the depth of the upstream end portion 114a.
- the other tab 116, or downstream tab has a meridian section substantially T-shaped coated and extends downstream from the downstream end of the base 112.
- upstream and downstream are used herein with reference to the flow direction of the gas flow in the turbine (arrow F in Fig. 1).
- the ring support structure 13 which is integral with the turbine casing 30 comprises an annular upstream radial flange 32 carrying an annular-shaped wedge-shaped hook 34 in the shape of a comma directed in the axial direction downstream, being able to 115.
- the mounting of the end portion 34a of the hook 34 in the housing 115 is designed to ensure the sealing between the flow stream of the gas flow and the outside of the sectors. ring 100, the upstream side thereof.
- the ring support structure 13 comprises an annular flange 36 with an inverted L-shaped section terminating in an annular support portion 36a against which the annular end portion 116a of the lug 116 rests.
- the end portion 116a of the tab 116 and the abutment portion 36a of the flange 36 are held without play against each other by means of a pliers 38 with a lying U-shaped meridian section. forming a circlip, in a manner known per se.
- the clamp 38 is immobilized circumferentially with respect to the flange 36 and the lug 116 by being inserted between fingers 36b and 116b protruding downstream from the portion 36a of the flange 36 and from the portion end 116a of the tab 116.
- a seal 20 is compressed between the bearing portion 36a of the flange 36 and the end portion 116a of the tab 116.
- the seal 20 is for example constituted by a metal braid immobilized in a housing formed in the inner face of the bearing portion 36a.
- inter-sector sealing is ensured by sealing tongues 22 housed in each ring sector 100, the interior of the base 112, in its median part, over almost the entire length (from upstream to downstream) of the base 112.
- the ring sectors 100 as described must have a significant thickness so that the parts made of CMC, which surround the sealing tongue and which also form the two tabs 114 and 116, are sufficiently resistant to withstand the thermomechanical stresses of operation.
- a fibrous preform for a turbine ring sector obtained by three-dimensional weaving and having a first base portion, two L-shaped portions forming a leg and having a first branch and a second branch.
- said first branch extending each of the two lateral ends of the first part, and a second part interconnecting the two tabs, thanks to a first connection formed between the second part and one of the two tabs and a second connection formed between the second portion and the other of the two legs, this second portion delimiting, with the legs and the first part, a cavity, a first band and a second band woven together forming the first branch, a first portion of the thickness of the second branch and the first part with, between them, a debonding zone situated in the first branch and the first part, and a third woven strip forming the second portion and a second portion of the thickness of the second leg of each leg.
- the location of at least one of the first link and the second link, formed between the second part (namely the third band) and the two legs, is located substantially between the first branch and the second branch;
- the second branch of each tab is formed of the superposition between a portion of the assembly formed of the first band and the second band and a portion of the third band.
- FIG. 1 is a half-sectional meridian view showing a turbine ring assembly according to the prior art
- FIG. 2 is a perspective view of a fiber preform according to the invention
- FIGS. 3 to 7 are enlarged representations of the weave planes of zones III to VII of FIG. 2, and
- Figure 8 is a view similar to that of Figure 2 showing the mounting of the metal strips of the turbine ring sector.
- Each ring sector according to the invention is made of CMC by forming a fibrous preform 40 (see FIG. 2) having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix.
- 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 threads.
- This fibrous preform 40 results from a blank which is produced by three-dimensional weaving, or multilayer weaving, with development of debonding zones to separate between them the preform parts which receive the metal strips forming the sealing tongues.
- upstream and downstream are used herein with reference to the direction of weaving (arrow T in Fig. 2).
- the first band A and the second band B are woven together with common weft threads traversing the entire thickness of the assembly formed of the first band A and the second band B, in order to interconnect all the layers of the strands. chain, and this in a first section T1, and in a fourth section T4 of the preform 40 (see Figures 2, 3 and 7).
- the first strip A and the second strip B are woven together with independent weft threads for each strip A and B, so that a space is provided between the first band A and the second band B, which constitutes a debonding zone D.
- the third band C of the preform 40 (see FIGS. 2, 4 and 7) is knitted parallel to the assembly formed by the first band A and the second band B, separately and independently, except in the second section T2. transition of the preform 40: at this location, the warp son of the assembly formed of the first band A and the second band B intersect the warp son of the third band C. Regarding the weft son, those of the third band C remain attached to the latter while those of the assembly formed of the first band A and the second band B, connect together all the layers of the warp son of the assembly formed of the first band A and of the second band B before the aforementioned crossing (at the top in FIG.
- the third band C it is defined, from upstream to downstream, a first section 48a disposed facing the first section T1 of the preform 40, a second section 48b disposed facing the third section T3 of the preform 40, and a third section 48c disposed opposite the fourth section T4 of the preform 40.
- FIGS. 3 to 7 show in chain section (orthogonal to the direction T of FIG. 2) examples of successive weave planes for the weaving respectively of the zones of details III to VII of FIG.
- the total number of warp layers is two for each band A, B, or C.
- the third band C is shorter than the set formed by the first band A and the second band B, because this third band C remains almost horizontal while the assembly formed of the first band A and the second band B has, after shaping the preform 40 (see Figure 2) the shape of the cross section of a jar of yogurt, namely a U with vertical branches slightly flared and whose free end is extended by two horizontal arms.
- the weave can be interlock type, as illustrated.
- Other weaves of three-dimensional weave or multilayer can be used as for example multi-web or multi-satin weaves. Reference may be made to WO2006136755.
- the blank may be shaped to obtain the ring sector preform 40 without cutting son, especially warp son.
- a first part 42 or base whose internal face is intended to form the internal face of the ring, resulting from a central portion of the third section T3 of the assembly formed by the first strip A and the second strip B and delimiting a first portion of the debonding zone D,
- first branches 44a and 46a correspond to the two lateral portions of the third section T3 of the assembly formed by the first band A and the second band B and respectively delimit a second portion portion and a third portion portion of the debonding zone D.
- the second branch 44b of the upstream tab 44 which is opposite the first section T1 of the preform 40, results from the superposition of an upstream lateral section of the assembly formed by the first strip A and the second band B (above) and an upstream lateral section 48a of the third band C (below).
- the second branch 46b of the downstream tab 46 which faces the fourth section T4 of the preform 40, results from the superposition of a downstream lateral section of the assembly formed by the first band A and the second band B ( below) and a downstream lateral section 48c of the third band C (above), and
- a second part 48b forming an outer wall and intended to interconnect the two tabs 44 and 46 at a distance and parallel to the first part 42.
- a first connection between the second part 48b and the upstream leg 44 is formed by the crossing presented above and resulting from the weaving of the three bands A, B and C.
- the third band C is connected forming the second part 48b and one of the two legs (upstream leg 44).
- the second link between the second portion 48b and the downstream leg 46 is embodied by a connection between the third band C and the assembly formed by the first band A and the second band B at the level of the other leg ( downstream leg 46).
- said second connection is made by stitching
- a sewing thread 49 traverses the entire thickness of the three strips A, B and C at the level of the downstream tab 46, which provides a quick and easy means of freezing the structure of the preform 40.
- This sewing thread 49 also makes it possible to close the cavity 60 delimited between the first leg 46a of the downstream leg, the first part 42, the first leg 44a of the upstream leg 44 and the second part 48b.
- a method of manufacturing a fibrous preform 40 is used for a one-piece turbine ring sector made of a ceramic matrix composite material comprising a first portion 42 forming a base and whose two lateral ends each extend by an L-shaped portion forming a leg (upstream portion 44, downstream portion 46) and having a first leg (44a, 46a) and a second leg (44b, 46b), and a second portion (48b) connecting between them the two tabs 44 and 46 and able to define, with the tabs 44 and 46 and the first part 42, a cavity 60, the method preferably comprising the following steps:
- the first band A and the second band B being woven parallel to each other, so as to form the first part 42, the first branch (44a, 46a) of the legs (44, 46) and a first portion; the thickness of the second limb (44b, 46b) of the tabs (44, 46), the first band A and the second band B being bonded together to form an assembly at the second limb (44b, 46b) ) and forming between them a debonding zone D at the location of the first part 42 and the first leg (44a, 46a) of the tabs (44, 46)
- the third band C is woven by crossing said third band C with the set formed by the first band A and the second band B at one of the legs (upstream leg 44), in order to connect the third band C forming the second part 48b and one of the two legs (upstream leg 44a), and
- connection is made between the third band C and the assembly formed of the first band A and the second band B at the other of the tabs (downstream leg 46a).
- this connection is obtained by sewing the yarn 49 all along the second branch 46b of the downstream tab 46.
- the method further comprises a further step of placing metal lamellae 50 in said debonding zone D (see FIG. 8).
- these metal strips 50 are in the form of three lamellae with:
- a second lamella 54 in the shape of an inverted L, a long branch of which is placed in the second portion of the debonding zone D situated opposite the first branch 44a of the upstream tab 44, and a short branch covering the upstream edge of the first lamella 52, and
- a third inverted L-shaped slat 56 having a long branch which is placed in the third portion of the debonding zone D situated opposite the first branch 46a of the downstream tab 46, and a short branch covering the downstream edge of the the first lamella 52.
- a consolidation composition typically a resin which may be diluted in a solvent
- the ring sector mounting mode obtained from such a preform 40 is similar to that implemented in the case of Figure 1. More precisely, in this case:
- the second branch 46b of the downstream tab 46 is housed in the clamp 38, bearing against the annular support portion 36a of the annular flange, and
- the second branch 44b of the upstream tab 44 is housed in a hook which is placed at the same location as the hook 34 of Figure 1 but which has a U-shape open towards the downstream.
- a turbine ring assembly comprising a plurality of ring sectors as presented in the preceding paragraphs and a ring support structure.
- the first portions 42 of the fibrous preforms 40 constitute an annular inner wall
- the second portions 48b of the fibrous preforms 40 constitute an annular outer wall
- the end of the second leg 44b, 46b of the two tabs 44, 46 is engaged in a housing of the ring support structure.
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- Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- General Engineering & Computer Science (AREA)
- Woven Fabrics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Ceramic Products (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2012141883/05A RU2553907C2 (ru) | 2010-03-02 | 2011-03-01 | Волоконная заготовка для кольцевого сектора турбины и способ ее изготовления |
CN201180012277.0A CN102933757B (zh) | 2010-03-02 | 2011-03-01 | 用于涡轮机环转扇形体的纤维预制件及其制造方法 |
US13/582,072 US9581039B2 (en) | 2010-03-02 | 2011-03-01 | Fiber preform for a turbine ring sector, and its method of fabrication |
BR112012022110A BR112012022110A2 (pt) | 2010-03-02 | 2011-03-01 | pré-forma fibrosa para um setor de anel de turbina e seu método de fabricação |
EP11712947.8A EP2542713B1 (fr) | 2010-03-02 | 2011-03-01 | Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication |
JP2012555471A JP5745548B2 (ja) | 2010-03-02 | 2011-03-01 | タービンリングセクタ用繊維プリフォームおよびその製造方法 |
CA2791644A CA2791644A1 (fr) | 2010-03-02 | 2011-03-01 | Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1051494A FR2957093B1 (fr) | 2010-03-02 | 2010-03-02 | Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication. |
FR1051494 | 2010-03-02 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011107708A1 true WO2011107708A1 (fr) | 2011-09-09 |
Family
ID=42235654
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2011/050428 WO2011107708A1 (fr) | 2010-03-02 | 2011-03-01 | Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication |
Country Status (9)
Country | Link |
---|---|
US (1) | US9581039B2 (fr) |
EP (1) | EP2542713B1 (fr) |
JP (1) | JP5745548B2 (fr) |
CN (1) | CN102933757B (fr) |
BR (1) | BR112012022110A2 (fr) |
CA (1) | CA2791644A1 (fr) |
FR (1) | FR2957093B1 (fr) |
RU (1) | RU2553907C2 (fr) |
WO (1) | WO2011107708A1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104395515A (zh) * | 2012-04-26 | 2015-03-04 | 斯奈克玛 | 通过三维编织方法编织的单件的纤维坯件用于制备涡轮发动机风扇的用复合材料制成的封闭盒结构平台 |
WO2019074881A1 (fr) * | 2017-10-12 | 2019-04-18 | Albany Engineered Composites, Inc. | Préformes tissées tridimensionnelles pour raidisseurs en oméga |
RU2795562C2 (ru) * | 2017-10-12 | 2023-05-05 | Олбэни Энджиниред Композитс, Инк. | Трехмерные тканые заготовки для омегаобразных элементов жесткости |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013063703A1 (fr) * | 2011-11-03 | 2013-05-10 | Groupe Ctt Inc. | Procédé de fabrication d'une ébauche tissée à fils de trame orientés |
WO2014151066A1 (fr) * | 2013-03-15 | 2014-09-25 | Chamberlain Adam L | Optimisation d'une architecture à fibres pour composites à matrice en céramique |
FR3018286B1 (fr) * | 2014-03-10 | 2016-05-27 | Aircelle Sa | Preforme tissee pour realiser un renfort circonferentiel ou torique a section en omega |
JP5874802B1 (ja) * | 2014-11-25 | 2016-03-02 | 株式会社豊田自動織機 | 繊維構造体及び繊維強化複合材 |
FR3029563B1 (fr) * | 2014-12-08 | 2020-01-17 | Safran Aircraft Engines | Plateforme a faible rapport de moyeu |
US10458433B2 (en) | 2015-06-17 | 2019-10-29 | United Technologies Corporation | Co-molded metallic fan case containment ring |
FR3044253B1 (fr) | 2015-11-26 | 2018-05-18 | Safran Aircraft Engines | Moule pour la fabrication d'un carter de soufflante de turbine a gaz en materiau composite et procede de fermeture d'un tel moule |
FR3055624B1 (fr) * | 2016-09-08 | 2019-11-22 | Safran Ceramics | Preforme fibreuse pour fabriquer une piece en materiau composite et procede associe |
US10801108B2 (en) * | 2017-08-28 | 2020-10-13 | Raytheon Technologies Corporation | Method for fabricating ceramic matrix composite components |
US10822281B2 (en) * | 2018-11-09 | 2020-11-03 | Raytheon Technologies Corporation | Accelerated CVI densification of CMC through infiltration |
US11359505B2 (en) * | 2019-05-04 | 2022-06-14 | Raytheon Technologies Corporation | Nesting CMC components |
CN112267917B (zh) * | 2020-09-18 | 2022-09-23 | 中国航发四川燃气涡轮研究院 | 一种纤维预制体以及陶瓷基复合材料涡轮外环 |
CN112538679B (zh) * | 2020-11-02 | 2022-07-12 | 南京玻璃纤维研究设计院有限公司 | 一种中空盒状增强体及其制备方法、中空盒的制备方法 |
CN114483207B (zh) * | 2021-12-29 | 2024-03-08 | 西安鑫垚陶瓷复合材料股份有限公司 | 陶瓷基复合材料涡轮外环预制体、定型模具及其使用方法 |
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US3102559A (en) * | 1959-12-24 | 1963-09-03 | Raymond Dev Ind Inc | Woven honeycomb cellular fabrics |
US3943980A (en) * | 1972-09-20 | 1976-03-16 | Hitco | Multi-ply woven article having double ribs |
US4686134A (en) * | 1984-12-29 | 1987-08-11 | Nippon Mayer Co., Ltd. | Three-dimensional structural member |
US4922968A (en) * | 1987-09-26 | 1990-05-08 | Vorwerk & Co. Interholding Gmbh | Premolding consisting of multiply fabric |
WO2009100737A1 (fr) * | 2008-02-14 | 2009-08-20 | Antica Valserchio S.R.L. | Tissu constitué d’au moins deux nappes entrelacées le long d’un extensible commun et procédé de production associé |
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US3090406A (en) * | 1961-02-23 | 1963-05-21 | Raymond Dev Ind Inc | Woven panel and method of making same |
US3481427A (en) * | 1968-11-29 | 1969-12-02 | Mc Donnell Douglas Corp | Acoustical panel structure |
AU8101491A (en) * | 1990-06-29 | 1992-01-23 | Gui Gerard De Jager | A process for manufacturing reinforced composites and filament material for use in said process |
FR2800797B1 (fr) * | 1999-11-10 | 2001-12-07 | Snecma | Assemblage d'un anneau bordant une turbine a la structure de turbine |
JP2004036443A (ja) * | 2002-07-02 | 2004-02-05 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンシュラウド構造 |
JP4385660B2 (ja) * | 2003-06-20 | 2009-12-16 | 株式会社Ihi | タービンシュラウドの回り止め構造 |
FR2861143B1 (fr) * | 2003-10-20 | 2006-01-20 | Snecma Moteurs | Aube de turbomachine, notamment aube de soufflante et son procede de fabrication |
US7147432B2 (en) | 2003-11-24 | 2006-12-12 | General Electric Company | Turbine shroud asymmetrical cooling elements |
RU2280767C2 (ru) * | 2004-10-14 | 2006-07-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Способ изготовления рабочего колеса турбины из композиционных материалов |
FR2887601B1 (fr) * | 2005-06-24 | 2007-10-05 | Snecma Moteurs Sa | Piece mecanique et procede de fabrication d'une telle piece |
FR2907841B1 (fr) * | 2006-10-30 | 2011-04-15 | Snecma | Secteur d'anneau de turbine de turbomachine |
FR2913053B1 (fr) * | 2007-02-23 | 2009-05-22 | Snecma Sa | Procede de fabrication d'un carter de turbine a gaz en materiau composite et carter ainsi obtenu |
JP5646517B2 (ja) * | 2009-03-09 | 2014-12-24 | スネクマ | タービンリング組立体 |
-
2010
- 2010-03-02 FR FR1051494A patent/FR2957093B1/fr active Active
-
2011
- 2011-03-01 CA CA2791644A patent/CA2791644A1/fr not_active Abandoned
- 2011-03-01 RU RU2012141883/05A patent/RU2553907C2/ru not_active IP Right Cessation
- 2011-03-01 WO PCT/FR2011/050428 patent/WO2011107708A1/fr active Application Filing
- 2011-03-01 JP JP2012555471A patent/JP5745548B2/ja not_active Expired - Fee Related
- 2011-03-01 BR BR112012022110A patent/BR112012022110A2/pt not_active IP Right Cessation
- 2011-03-01 EP EP11712947.8A patent/EP2542713B1/fr active Active
- 2011-03-01 US US13/582,072 patent/US9581039B2/en active Active
- 2011-03-01 CN CN201180012277.0A patent/CN102933757B/zh not_active Expired - Fee Related
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US3102559A (en) * | 1959-12-24 | 1963-09-03 | Raymond Dev Ind Inc | Woven honeycomb cellular fabrics |
US3943980A (en) * | 1972-09-20 | 1976-03-16 | Hitco | Multi-ply woven article having double ribs |
US4686134A (en) * | 1984-12-29 | 1987-08-11 | Nippon Mayer Co., Ltd. | Three-dimensional structural member |
US4922968A (en) * | 1987-09-26 | 1990-05-08 | Vorwerk & Co. Interholding Gmbh | Premolding consisting of multiply fabric |
WO2009100737A1 (fr) * | 2008-02-14 | 2009-08-20 | Antica Valserchio S.R.L. | Tissu constitué d’au moins deux nappes entrelacées le long d’un extensible commun et procédé de production associé |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104395515A (zh) * | 2012-04-26 | 2015-03-04 | 斯奈克玛 | 通过三维编织方法编织的单件的纤维坯件用于制备涡轮发动机风扇的用复合材料制成的封闭盒结构平台 |
WO2019074881A1 (fr) * | 2017-10-12 | 2019-04-18 | Albany Engineered Composites, Inc. | Préformes tissées tridimensionnelles pour raidisseurs en oméga |
KR20200066312A (ko) | 2017-10-12 | 2020-06-09 | 알바니 엔지니어드 콤포짓스, 인크. | 오메가 보강재를 위한 3차원 제직 예비성형체 |
US11192312B2 (en) | 2017-10-12 | 2021-12-07 | Albany Engineered Composites, Inc. | Three-dimensional woven preforms for omega stiffeners |
EP4035858A1 (fr) * | 2017-10-12 | 2022-08-03 | Albany Engineered Composites, Inc. | Préformes tissées tridimensionnelles pour raidisseurs en oméga |
RU2795562C2 (ru) * | 2017-10-12 | 2023-05-05 | Олбэни Энджиниред Композитс, Инк. | Трехмерные тканые заготовки для омегаобразных элементов жесткости |
Also Published As
Publication number | Publication date |
---|---|
US9581039B2 (en) | 2017-02-28 |
US20130108417A1 (en) | 2013-05-02 |
JP5745548B2 (ja) | 2015-07-08 |
BR112012022110A2 (pt) | 2017-11-28 |
CN102933757B (zh) | 2014-06-18 |
EP2542713B1 (fr) | 2015-05-13 |
RU2012141883A (ru) | 2014-04-10 |
EP2542713A1 (fr) | 2013-01-09 |
JP2013521209A (ja) | 2013-06-10 |
RU2553907C2 (ru) | 2015-06-20 |
CN102933757A (zh) | 2013-02-13 |
CA2791644A1 (fr) | 2011-09-09 |
FR2957093B1 (fr) | 2012-03-23 |
FR2957093A1 (fr) | 2011-09-09 |
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