US20140004293A1 - Ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component - Google Patents
Ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component Download PDFInfo
- Publication number
- US20140004293A1 US20140004293A1 US13/803,452 US201313803452A US2014004293A1 US 20140004293 A1 US20140004293 A1 US 20140004293A1 US 201313803452 A US201313803452 A US 201313803452A US 2014004293 A1 US2014004293 A1 US 2014004293A1
- Authority
- US
- United States
- Prior art keywords
- cmc
- ceramic matrix
- matrix composite
- component
- metal interface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
-
- 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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic materials
-
- 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- 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
- Y10T29/49229—Prime mover or fluid pump making
- Y10T29/49236—Fluid pump or compressor making
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24008—Structurally defined web or sheet [e.g., overall dimension, etc.] including fastener for attaching to external surface
Definitions
- the present invention relates generally to turbines. More specifically, to a ceramic matrix composite (CMC) component and a method of attaching a metal seal to the ceramic matrix composite component.
- CMC ceramic matrix composite
- CMC ceramic matrix composites
- CMC turbine blades are produced by initially providing plies of balanced two-dimensional (2D) woven cloth comprising silicon carbide (SiC)-containing fibers, having two weave directions at substantially 90° angles to each other, with substantially the same number of fibers running in both directions of the weave.
- 2D two-dimensional
- SiC silicon carbide
- Such turbine components require attachment to adjoining metallic hardware and/or metallic surfaces.
- Two disadvantages associated with attaching a CMC to metallic hardware are the wear of the metallic hardware by the hard, abrasive ceramic material surface, and the lack of load distribution in the CMC. Load distribution is critical in the interfaces between the CMC components and metal surfaces, such as shrouds.
- metallic shims or ceramic cloths have been interposed between the CMC and metallic surfaces to improve load distribution. Wear is typically reduced by the application of coatings to the metallic hardware or coatings to the nozzle attachment surfaces.
- CMC ceramic matrix composite
- a ceramic matrix composite component is provided.
- the ceramic matrix composite component includes a first end and a second end.
- the ceramic matrix composite component includes a CMC metal interface member attached to the second end.
- the CMC metal interface member is operable to join to a static seal in a gas turbine.
- a method of attaching a static seal to a ceramic matrix composite component includes providing a ceramic matrix composite component having a first end and a second end.
- the method includes providing a CMC metal interface member.
- the method includes attaching the CMC metal interface member to the second end of the ceramic matrix composite component.
- the method includes providing a static seal and joining the static seal to the CMC metal interface member.
- the CMC metal interface member forms a plenum for purging rotor air.
- FIG. 1 is a perspective schematic section view of a CMC component of the present disclosure.
- FIG. 2 is a perspective schematic section view of a CMC component of the present disclosure.
- FIG. 3 is a schematic top partial view of a CMC component of the present disclosure.
- FIG. 4 is a flow chart of the method of attaching a static seal to a CMC component of the present disclosure.
- CMC ceramic matrix composite
- One aspect of an embodiment of the present disclosure includes providing a honeycomb seal attachment for a CMC component. Another aspect of the present disclosure is that the system allows for different thermal growth of the CMC component and the CMC metal interface member. Yet another aspect of the present disclosure is that the system provides airfoil cavity sealing. Another aspect of the present disclosure is that the system provides a plenum to feed rotor purge air.
- FIGS. 1 and 2 are perspective schematic section views of a CMC component 10 .
- CMC component may include a first end 14 and a second end 16 opposite the first end.
- CMC component 10 may include an impingement baffle cavity surrounded by outer layers 12 .
- CMC component 10 may be a non-rotating component, such as, but not limited to, vanes or nozzles.
- CMC component 10 may be a nozzle.
- CMC component 10 may be attached to a nozzle hanger 80 .
- Nozzle hanger 80 may be attached by any suitable means to a case 90 of a gas turbine.
- CMC component 10 may be adjacent to rotating blades 100 in gas turbine.
- CMC component may include a CMC metal interface member attached to second end of CMC component creating a plenum underneath CMC component to distribute air when needed for rotor purge.
- CMC component 10 may include a CMC metal interface member 50 or seal box attached to second end 16 of CMC component 10 .
- CMC metal interface member 50 may create a plenum underneath CMC component 10 to distribute air when needed for rotor purge.
- the air used to purge the rotor is the arrow labeled 120 .
- CMC metal interface member 50 may span a single CMC component 10 .
- CMC metal interface member 50 may span a number of CMC components 10 and may span up to a full 360 degree ring around CMC component 10 .
- Material for CMC metal interface member 50 may include, but is not limited to, metals, metal alloys, and combinations thereof, for example the alloys may include nickel-based superalloys, cobalt-based superalloys, and combinations thereof.
- CMC metal interface 50 may include a feed tube 64 that exits into a channel 54 adjacent to static seal 40 .
- feed tube 60 may protrude from CMC metal interface 50 into impingement baffle cavity 30 .
- feed tube 64 may extend down from impingement baffle cavity 30 into CMC metal interface 50 .
- attachment member 70 instead of using feed tube 64 , to create plenum, attachment member 70 may include a channel or aperture (not shown) to receive rotor purge air 120 .
- CMC metal interface 50 may be unpressurized.
- CMC metal interface member may include an attachment member.
- CMC metal interface member 50 includes an attachment member 70 .
- Attachment member 70 may be attached to CMC metal interface member 50 by any suitable means, such as, but not limited to, tapping attachment member 70 into CMC metal interface member 50 , using a nut to secure attachment member 70 to CMC metal interface member 50 , using an insert to secure attachment member 70 to CMC metal interface member 50 .
- Material for attachment member 70 may include, but is not limited to, metals, metal alloys, and combinations thereof, for example the alloys may include nickel-based superalloys, cobalt-based superalloys, and combinations thereof.
- CMC metal interface member may attach to CMC component by attachment member.
- CMC metal interface member 50 may attach to CMC component 10 by attachment member 70 .
- attachment member 70 may attach to impingement baffle cavity 30 of CMC component 10 .
- attachment member 70 may be a bolt of any desired length.
- impingement baffle cavity 30 may include an aperture (not shown) for receiving attachment member, where the aperture may be threaded to receive attachment member 70 .
- attachment member 70 may not be secured in impingement baffle cavity 30 , instead a nut or other stopping member may be used to hold attachment member 70 securely in place at second end 16 of CMC component 10 .
- CMC metal interface member may provide a surface to join static seal to CMC component.
- CMC metal interface member 50 may provide a surface to join a static seal 40 to CMC component 10 .
- Static seal 40 may be attached to CMC metal interface member 50 by any suitable joining means, such as, but not limited to, brazing and welding. Joint 46 between CMC metal interface 50 and static seal 40 is shown in FIGS. 1 and 2 .
- static seal 40 may be a honeycomb seal.
- Material for static seal 40 may be selected from, but not limited to, metals, metal alloys, and combinations thereof, for example, the alloys may include nickel-based superalloys, cobalt-based superalloys, and combinations thereof.
- Static seal 40 may be adjacent rotating seals 110 in gas turbine.
- a method of attaching a metal seal to a ceramic matrix component may include using a CMC interface member and a static seal.
- FIG. 4 depicts a flow chart of a method 400 of attaching metal seal 40 to ceramic matrix composite component 10 .
- Method 400 may include providing ceramic matrix composite component 10 having first end 14 and second end 16 , step 401 (see FIGS. 1 and 2 ).
- Method 400 may include providing CMC metal interface member 50 , step 403 (see FIGS. 1 and 2 ).
- Method 400 may include attaching CMC metal interface member 50 to second end 16 of ceramic matrix composite component 10 , step 405 (see FIGS. 1 and 2 ).
- Method 400 may include providing static seal 40 , step 407 (see FIGS. 1 and 2 ).
- Method 400 may include joining static seal 40 to CMC metal interface member 50 , step 409 (see FIGS. 1 and 2 ).
- CMC metal interface member 50 may form a plenum for purging rotor air and may provide a surface to attach static seal 40 , which may be metal, to CMC component 10 .
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Composite Materials (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Ceramic Products (AREA)
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/803,452 US20140004293A1 (en) | 2012-06-30 | 2013-03-14 | Ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component |
EP13729228.0A EP2867182A1 (en) | 2012-06-30 | 2013-06-06 | A ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component |
CN201380035129.XA CN104379536B (zh) | 2012-06-30 | 2013-06-06 | 陶瓷基质复合物构件和将静密封件附接至陶瓷基质复合物构件的方法 |
PCT/US2013/044438 WO2014004017A1 (en) | 2012-06-30 | 2013-06-06 | A ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component |
CA2877273A CA2877273A1 (en) | 2012-06-30 | 2013-06-06 | A ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component |
JP2015520223A JP6329536B2 (ja) | 2012-06-30 | 2013-06-06 | セラミックマトリックス複合材料部品並びに静止シールをセラミックマトリックス複合材料部品に取り付ける方法 |
BR112015000084A BR112015000084A2 (pt) | 2012-06-30 | 2013-06-06 | componente de compósito de matriz cerâmica e método para ligar uma vedação metálica. |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201261666815P | 2012-06-30 | 2012-06-30 | |
US13/803,452 US20140004293A1 (en) | 2012-06-30 | 2013-03-14 | Ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component |
Publications (1)
Publication Number | Publication Date |
---|---|
US20140004293A1 true US20140004293A1 (en) | 2014-01-02 |
Family
ID=49778446
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/803,452 Abandoned US20140004293A1 (en) | 2012-06-30 | 2013-03-14 | Ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component |
Country Status (7)
Country | Link |
---|---|
US (1) | US20140004293A1 (zh) |
EP (1) | EP2867182A1 (zh) |
JP (1) | JP6329536B2 (zh) |
CN (1) | CN104379536B (zh) |
BR (1) | BR112015000084A2 (zh) |
CA (1) | CA2877273A1 (zh) |
WO (1) | WO2014004017A1 (zh) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150345388A1 (en) * | 2014-06-02 | 2015-12-03 | General Electric Company | Gas turbine component and process for producing gas turbine component |
EP3112599A1 (en) * | 2015-07-02 | 2017-01-04 | United Technologies Corporation | Transfer tube and turbine section comprising transfer tube |
FR3040734A1 (fr) * | 2015-09-09 | 2017-03-10 | Snecma | Turbine de turbomachine comprenant un etage distributeur en materiau composite a matrice ceramique |
US20170252896A1 (en) * | 2014-09-17 | 2017-09-07 | Europe Technologies | Method for treating a composite part |
US20180037511A1 (en) * | 2015-06-10 | 2018-02-08 | Ihi Corporation | Turbine |
EP3670843A1 (en) * | 2018-12-21 | 2020-06-24 | Rolls-Royce plc | Turbine section of a gas turbine engine with ceramic matrix composite vanes |
US10711630B2 (en) | 2018-03-20 | 2020-07-14 | Honeywell International Inc. | Retention and control system for turbine shroud ring |
US10753232B2 (en) | 2017-06-16 | 2020-08-25 | General Electric Company | Assemblies and methods for cooling flowpath support structure and flowpath components |
US20200340365A1 (en) * | 2019-04-23 | 2020-10-29 | Rolls-Royce Plc | Turbine section assembly with ceramic matrix composite vane |
US11261747B2 (en) * | 2019-05-17 | 2022-03-01 | Rolls-Royce Plc | Ceramic matrix composite vane with added platform |
US20230051167A1 (en) * | 2020-01-23 | 2023-02-16 | Safran Aircraft Engines | Turbomachine stator assembly comprising an inner shroud having upstream and downstream portions assembled by axial translation |
US11879362B1 (en) | 2023-02-21 | 2024-01-23 | Rolls-Royce Corporation | Segmented ceramic matrix composite vane endwall integration with turbine shroud ring and mounting thereof |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10202857B2 (en) | 2015-02-06 | 2019-02-12 | United Technologies Corporation | Vane stages |
US10161257B2 (en) * | 2015-10-20 | 2018-12-25 | General Electric Company | Turbine slotted arcuate leaf seal |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2963307A (en) * | 1954-12-28 | 1960-12-06 | Gen Electric | Honeycomb seal |
US5143383A (en) * | 1984-06-04 | 1992-09-01 | General Electric Company | Stepped tooth rotating labyrinth seal |
US5215435A (en) * | 1991-10-28 | 1993-06-01 | General Electric Company | Angled cooling air bypass slots in honeycomb seals |
US5749701A (en) * | 1996-10-28 | 1998-05-12 | General Electric Company | Interstage seal assembly for a turbine |
US20030180141A1 (en) * | 2002-03-22 | 2003-09-25 | Kress Jeffrey Allen | Band cooled turbine nozzle |
US20040120811A1 (en) * | 2002-12-20 | 2004-06-24 | Darkins Toby George | Methods and apparatus for securing multi-piece nozzle assemblies |
US20040170498A1 (en) * | 2003-02-27 | 2004-09-02 | Peterman Jonathan Jordan | Gas turbine engine turbine nozzle bifurcated impingement baffle |
US20070280822A1 (en) * | 2006-06-06 | 2007-12-06 | United Technologies Corporation | Ceramic matrix composite capped bolt attachment |
US20080181766A1 (en) * | 2005-01-18 | 2008-07-31 | Siemens Westinghouse Power Corporation | Ceramic matrix composite vane with chordwise stiffener |
US20100068034A1 (en) * | 2008-09-18 | 2010-03-18 | Schiavo Anthony L | CMC Vane Assembly Apparatus and Method |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6558114B1 (en) * | 2000-09-29 | 2003-05-06 | Siemens Westinghouse Power Corporation | Gas turbine with baffle reducing hot gas ingress into interstage disc cavity |
US6394537B1 (en) * | 2001-01-31 | 2002-05-28 | Daimlerchrysler Corporation | Arrangement for attaching a plastic vehicle body to a metal frame and related method |
US7153054B2 (en) * | 2004-05-20 | 2006-12-26 | United Technologies Corporation | Fastener assembly for attaching a non-metal component to a metal component |
US7546743B2 (en) * | 2005-10-12 | 2009-06-16 | General Electric Company | Bolting configuration for joining ceramic combustor liner to metal mounting attachments |
US7874059B2 (en) * | 2006-01-12 | 2011-01-25 | Siemens Energy, Inc. | Attachment for ceramic matrix composite component |
US7824152B2 (en) * | 2007-05-09 | 2010-11-02 | Siemens Energy, Inc. | Multivane segment mounting arrangement for a gas turbine |
US8211524B1 (en) * | 2008-04-24 | 2012-07-03 | Siemens Energy, Inc. | CMC anchor for attaching a ceramic thermal barrier to metal |
US9011620B2 (en) * | 2009-09-11 | 2015-04-21 | Technip Process Technology, Inc. | Double transition joint for the joining of ceramics to metals |
US8454303B2 (en) * | 2010-01-14 | 2013-06-04 | General Electric Company | Turbine nozzle assembly |
US8770931B2 (en) * | 2011-05-26 | 2014-07-08 | United Technologies Corporation | Hybrid Ceramic Matrix Composite vane structures for a gas turbine engine |
US8864492B2 (en) * | 2011-06-23 | 2014-10-21 | United Technologies Corporation | Reverse flow combustor duct attachment |
-
2013
- 2013-03-14 US US13/803,452 patent/US20140004293A1/en not_active Abandoned
- 2013-06-06 JP JP2015520223A patent/JP6329536B2/ja not_active Expired - Fee Related
- 2013-06-06 EP EP13729228.0A patent/EP2867182A1/en not_active Withdrawn
- 2013-06-06 CN CN201380035129.XA patent/CN104379536B/zh not_active Expired - Fee Related
- 2013-06-06 CA CA2877273A patent/CA2877273A1/en not_active Abandoned
- 2013-06-06 WO PCT/US2013/044438 patent/WO2014004017A1/en active Application Filing
- 2013-06-06 BR BR112015000084A patent/BR112015000084A2/pt not_active Application Discontinuation
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2963307A (en) * | 1954-12-28 | 1960-12-06 | Gen Electric | Honeycomb seal |
US5143383A (en) * | 1984-06-04 | 1992-09-01 | General Electric Company | Stepped tooth rotating labyrinth seal |
US5215435A (en) * | 1991-10-28 | 1993-06-01 | General Electric Company | Angled cooling air bypass slots in honeycomb seals |
US5749701A (en) * | 1996-10-28 | 1998-05-12 | General Electric Company | Interstage seal assembly for a turbine |
US20030180141A1 (en) * | 2002-03-22 | 2003-09-25 | Kress Jeffrey Allen | Band cooled turbine nozzle |
US20040120811A1 (en) * | 2002-12-20 | 2004-06-24 | Darkins Toby George | Methods and apparatus for securing multi-piece nozzle assemblies |
US20040170498A1 (en) * | 2003-02-27 | 2004-09-02 | Peterman Jonathan Jordan | Gas turbine engine turbine nozzle bifurcated impingement baffle |
US20080181766A1 (en) * | 2005-01-18 | 2008-07-31 | Siemens Westinghouse Power Corporation | Ceramic matrix composite vane with chordwise stiffener |
US20070280822A1 (en) * | 2006-06-06 | 2007-12-06 | United Technologies Corporation | Ceramic matrix composite capped bolt attachment |
US20100068034A1 (en) * | 2008-09-18 | 2010-03-18 | Schiavo Anthony L | CMC Vane Assembly Apparatus and Method |
Non-Patent Citations (3)
Title |
---|
ASM International, "Chapter 2 Thermal Expansion", 2002, p.1-3; Accessed at http://www.asminternational.org/documents/10192/3449965/ACFAAD6.pdf/2d574bfc-e104-48c5-8d8e-c33ffe91c3a0.*Page numbers added by Examiner. * |
Muktinutalapati, N. "Materials for Gas Turbines - An Overview, Advances in Gas Turbine Technology"; Benini, E. (Ed.); 2011, p 293-314. * |
Oxford English Dictionary, "Clamp, v.1", p. 1-2, Accessed on 8/23/19 at https://oed.com/view/Entry/33719?isAdvanced=false&result=1&rskey=Xe6LoK&&print. * |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9719420B2 (en) * | 2014-06-02 | 2017-08-01 | General Electric Company | Gas turbine component and process for producing gas turbine component |
US20150345388A1 (en) * | 2014-06-02 | 2015-12-03 | General Electric Company | Gas turbine component and process for producing gas turbine component |
US20170252896A1 (en) * | 2014-09-17 | 2017-09-07 | Europe Technologies | Method for treating a composite part |
US10597334B2 (en) * | 2015-06-10 | 2020-03-24 | Ihi Corporation | Turbine comprising turbine stator vanes of a ceramic matrix composite attached to a turbine case |
US20180037511A1 (en) * | 2015-06-10 | 2018-02-08 | Ihi Corporation | Turbine |
US10018062B2 (en) | 2015-07-02 | 2018-07-10 | United Technologies Corporation | Axial transfer tube |
EP3112599A1 (en) * | 2015-07-02 | 2017-01-04 | United Technologies Corporation | Transfer tube and turbine section comprising transfer tube |
WO2017042461A1 (fr) * | 2015-09-09 | 2017-03-16 | Safran Aircraft Engines | Turbine de turbomachine comprenant un etage distributeur en materiau composite a matrice ceramique |
FR3040734A1 (fr) * | 2015-09-09 | 2017-03-10 | Snecma | Turbine de turbomachine comprenant un etage distributeur en materiau composite a matrice ceramique |
CN108026785A (zh) * | 2015-09-09 | 2018-05-11 | 赛峰航空器发动机 | 包含由陶瓷基复合材料制成的分配器级的涡轮发动机的涡轮机 |
US11193382B2 (en) | 2015-09-09 | 2021-12-07 | Safran Aircraft Engines | Turbine engine turbine including a nozzle stage made of ceramic matrix composite material |
US10753232B2 (en) | 2017-06-16 | 2020-08-25 | General Electric Company | Assemblies and methods for cooling flowpath support structure and flowpath components |
US10711630B2 (en) | 2018-03-20 | 2020-07-14 | Honeywell International Inc. | Retention and control system for turbine shroud ring |
EP3670843A1 (en) * | 2018-12-21 | 2020-06-24 | Rolls-Royce plc | Turbine section of a gas turbine engine with ceramic matrix composite vanes |
US10961857B2 (en) | 2018-12-21 | 2021-03-30 | Rolls-Royce Plc | Turbine section of a gas turbine engine with ceramic matrix composite vanes |
US10975708B2 (en) * | 2019-04-23 | 2021-04-13 | Rolls-Royce Plc | Turbine section assembly with ceramic matrix composite vane |
US20200340365A1 (en) * | 2019-04-23 | 2020-10-29 | Rolls-Royce Plc | Turbine section assembly with ceramic matrix composite vane |
US11261747B2 (en) * | 2019-05-17 | 2022-03-01 | Rolls-Royce Plc | Ceramic matrix composite vane with added platform |
US20230051167A1 (en) * | 2020-01-23 | 2023-02-16 | Safran Aircraft Engines | Turbomachine stator assembly comprising an inner shroud having upstream and downstream portions assembled by axial translation |
US11879362B1 (en) | 2023-02-21 | 2024-01-23 | Rolls-Royce Corporation | Segmented ceramic matrix composite vane endwall integration with turbine shroud ring and mounting thereof |
Also Published As
Publication number | Publication date |
---|---|
CN104379536A (zh) | 2015-02-25 |
CN104379536B (zh) | 2016-08-31 |
BR112015000084A2 (pt) | 2017-06-27 |
JP2015527521A (ja) | 2015-09-17 |
EP2867182A1 (en) | 2015-05-06 |
WO2014004017A1 (en) | 2014-01-03 |
CA2877273A1 (en) | 2014-01-03 |
JP6329536B2 (ja) | 2018-05-23 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20140004293A1 (en) | Ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component | |
US9546557B2 (en) | Nozzle, a nozzle hanger, and a ceramic to metal attachment system | |
US10612402B2 (en) | Method of assembly of bi-cast turbine vane | |
US8475695B2 (en) | Ceramic composite with integrated compliance/wear layer | |
US9175571B2 (en) | Connecting system for metal components and CMC components, a turbine blade retaining system and a rotating component retaining system | |
EP2971569B1 (en) | Gas turbine engine component including a compliant contact layer | |
US10415394B2 (en) | Gas turbine engine blade with ceramic tip and cooling arrangement | |
US20160312626A1 (en) | Method for fabricating a ceramic matrix composite rotor blade | |
US20170059159A1 (en) | Cmc combustor shell with integral chutes | |
US20190022753A1 (en) | Method for producing a component, and device | |
JP6442185B2 (ja) | タービンシステムおよびアダプタ | |
US8366386B2 (en) | Method and assembly for gas turbine engine airfoils with protective coating | |
JP7077060B2 (ja) | ハイブリッド被覆システムを有する構成要素および構成要素を形成するための方法 | |
US20220275728A1 (en) | Three-dimensional ceramic matrix composite t-joint for airfoils via pin-weaving |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GROOMS, JAMES HAMILTON;SENILE, DARRELL GLENN;FREDRICK, ROBERT ALAN;AND OTHERS;REEL/FRAME:030170/0687 Effective date: 20130313 |
|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GROOMS, JAMES HAMILTON, II;SENILE, DARRELL GLENN;FREDERICK, ROBERT ALAN;AND OTHERS;REEL/FRAME:034530/0029 Effective date: 20130313 |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: NON FINAL ACTION MAILED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: FINAL REJECTION MAILED |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |