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
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- 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.)
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Classifications
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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 .
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- 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)
Abstract
Description
- This patent application claims the benefit of U.S. Provisional Patent Application Ser. No. 61/666,815 filed on Jun. 30, 2012 and entitled “CERAMIC MATRIX COMPOSITE COMPONENT AND A METHOD OF ATTACHING A STATIC SEAL TO A CERAMIC MATRIX COMPOSITE COMPONENT,” the disclosure of which is incorporated by reference as if fully rewritten herein.
- 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.
- A number of techniques have been used in the past to manufacture turbine engine components, such as turbine blades or nozzles using ceramic matrix composites (CMC). One method of manufacturing CMC components relates to the production of silicon carbide matrix composites containing fibrous material that is infiltrated with molten silicon, herein referred to as the Silcomp process. The fibers generally have diameters of about 140 micrometers or greater, which prevents intricate, complex shapes, such as turbine blade components, to be manufactured by the Silcomp process.
- Another technique of manufacturing CMC turbine blades is the method known as the slurry cast melt infiltration (MI) process. In one method of manufacturing using the slurry cast MI method, CMCs 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.
- Generally, 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. Typically, 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.
- Therefore, a ceramic matrix composite (CMC) component and a method of attaching a metal seal to a CMC component that do not suffer from the above drawbacks is desirable in the art.
- According to an exemplary embodiment of the present disclosure, 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.
- According to another exemplary embodiment of the present disclosure, a method of attaching a static seal to a ceramic matrix composite component is provided. The method 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.
- Other features and advantages of the present invention will be apparent from the following more detailed description of the preferred embodiment, taken in conjunction with the accompanying drawings which illustrate, by way of example, the principles of the invention.
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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. - Wherever possible, the same reference numbers will be used throughout the drawings to represent the same parts.
- Provided is a ceramic matrix composite (CMC) component and a method of attaching a metal seal to the CMC component.
- 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.
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FIGS. 1 and 2 are perspective schematic section views of aCMC component 10. CMC component may include afirst end 14 and asecond end 16 opposite the first end.CMC component 10 may include an impingement baffle cavity surrounded byouter layers 12.CMC component 10 may be a non-rotating component, such as, but not limited to, vanes or nozzles. For example, as depicted in thefigures CMC component 10 may be a nozzle. In one embodiment,CMC component 10 may be attached to anozzle hanger 80.Nozzle hanger 80 may be attached by any suitable means to acase 90 of a gas turbine.CMC component 10 may be adjacent to rotatingblades 100 in gas turbine. - According to one embodiment, 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. For example, as shown in
FIGS. 1 and 2 ,CMC component 10 may include a CMCmetal interface member 50 or seal box attached tosecond end 16 ofCMC component 10. CMCmetal interface member 50 may create a plenum underneathCMC component 10 to distribute air when needed for rotor purge. As shown inFIG. 2 , the air used to purge the rotor is the arrow labeled 120. In one embodiment, as shown, CMCmetal interface member 50 may span asingle CMC component 10. In an alternative embodiment, CMCmetal interface member 50 may span a number ofCMC components 10 and may span up to a full 360 degree ring aroundCMC component 10. Material for CMCmetal 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 achannel 54 adjacent tostatic seal 40. For example, as shown inFIGS. 1 and 2 ,feed tube 60 may protrude fromCMC metal interface 50 intoimpingement baffle cavity 30. In an alternative embodiment, feed tube 64 may extend down fromimpingement baffle cavity 30 intoCMC metal interface 50. In another embodiment, instead of using feed tube 64, to create plenum,attachment member 70 may include a channel or aperture (not shown) to receiverotor purge air 120. In an alternative embodiment,CMC metal interface 50 may be unpressurized. - According to one embodiment, CMC metal interface member may include an attachment member. For example, as shown in
FIGS. 1 and 2 , CMCmetal interface member 50 includes anattachment member 70.Attachment member 70 may be attached to CMCmetal interface member 50 by any suitable means, such as, but not limited to, tappingattachment member 70 into CMCmetal interface member 50, using a nut to secureattachment member 70 to CMCmetal interface member 50, using an insert to secureattachment member 70 to CMCmetal interface member 50. Material forattachment 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. - According to one embodiment, CMC metal interface member may attach to CMC component by attachment member. For example, as shown in
FIGS. 1 and 2 , CMCmetal interface member 50 may attach toCMC component 10 byattachment member 70. As shown inFIG. 3 ,attachment member 70 may attach to impingementbaffle cavity 30 ofCMC component 10. In one embodiment,attachment member 70 may be a bolt of any desired length. In one embodiment,impingement baffle cavity 30 may include an aperture (not shown) for receiving attachment member, where the aperture may be threaded to receiveattachment member 70. In another embodiment,attachment member 70 may not be secured inimpingement baffle cavity 30, instead a nut or other stopping member may be used to holdattachment member 70 securely in place atsecond end 16 ofCMC component 10. - According to one embodiment, CMC metal interface member may provide a surface to join static seal to CMC component. For example, as shown in
FIGS. 1 and 2 , CMCmetal interface member 50 may provide a surface to join astatic seal 40 toCMC component 10.Static seal 40 may be attached to CMCmetal interface member 50 by any suitable joining means, such as, but not limited to, brazing and welding. Joint 46 betweenCMC metal interface 50 andstatic seal 40 is shown inFIGS. 1 and 2 . In one embodiment,static seal 40 may be a honeycomb seal. Material forstatic 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 adjacentrotating seals 110 in gas turbine. - According to one embodiment, a method of attaching a metal seal to a ceramic matrix component may include using a CMC interface member and a static seal. For example,
FIG. 4 depicts a flow chart of amethod 400 of attachingmetal seal 40 to ceramicmatrix composite component 10.Method 400 may include providing ceramicmatrix composite component 10 havingfirst end 14 andsecond end 16, step 401 (seeFIGS. 1 and 2 ).Method 400 may include providing CMCmetal interface member 50, step 403 (seeFIGS. 1 and 2 ).Method 400 may include attaching CMCmetal interface member 50 tosecond end 16 of ceramicmatrix composite component 10, step 405 (seeFIGS. 1 and 2 ).Method 400 may include providingstatic seal 40, step 407 (seeFIGS. 1 and 2 ).Method 400 may include joiningstatic seal 40 to CMCmetal interface member 50, step 409 (seeFIGS. 1 and 2 ). CMCmetal interface member 50 may form a plenum for purging rotor air and may provide a surface to attachstatic seal 40, which may be metal, toCMC component 10. - While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (12)
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
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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 |
CN201380035129.XA CN104379536B (en) | 2012-06-30 | 2013-06-06 | Ceramic matrix composite component and the method that static seal is attached to 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 |
JP2015520223A JP6329536B2 (en) | 2012-06-30 | 2013-06-06 | Ceramic matrix composite part and method for attaching a static seal to a ceramic matrix composite part |
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 |
BR112015000084A BR112015000084A2 (en) | 2012-06-30 | 2013-06-06 | ceramic matrix composite component and method for bonding a metal seal. |
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 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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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 |
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US20140004293A1 true US20140004293A1 (en) | 2014-01-02 |
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Family Applications (1)
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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 |
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US (1) | US20140004293A1 (en) |
EP (1) | EP2867182A1 (en) |
JP (1) | JP6329536B2 (en) |
CN (1) | CN104379536B (en) |
BR (1) | BR112015000084A2 (en) |
CA (1) | CA2877273A1 (en) |
WO (1) | WO2014004017A1 (en) |
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US10961857B2 (en) | 2018-12-21 | 2021-03-30 | Rolls-Royce Plc | Turbine section of a gas turbine engine with ceramic matrix composite vanes |
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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 (en) | 2015-02-25 |
JP6329536B2 (en) | 2018-05-23 |
EP2867182A1 (en) | 2015-05-06 |
CA2877273A1 (en) | 2014-01-03 |
WO2014004017A1 (en) | 2014-01-03 |
CN104379536B (en) | 2016-08-31 |
BR112015000084A2 (en) | 2017-06-27 |
JP2015527521A (en) | 2015-09-17 |
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