EP3317584A1 - Élément hybride comprenant un matériau composite à matrice céramique renforcé de métal - Google Patents

Élément hybride comprenant un matériau composite à matrice céramique renforcé de métal

Info

Publication number
EP3317584A1
EP3317584A1 EP15832842.7A EP15832842A EP3317584A1 EP 3317584 A1 EP3317584 A1 EP 3317584A1 EP 15832842 A EP15832842 A EP 15832842A EP 3317584 A1 EP3317584 A1 EP 3317584A1
Authority
EP
European Patent Office
Prior art keywords
metal skeleton
skeleton structure
component
cmc
metal
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.)
Withdrawn
Application number
EP15832842.7A
Other languages
German (de)
English (en)
Inventor
Zachary D. Dyer
Sachin R. Shinde
Phillip W. Gravett
Jay A. Morrison
Kimber-Lee BROWN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Inc
Original Assignee
Siemens Energy Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens Energy Inc filed Critical Siemens Energy Inc
Publication of EP3317584A1 publication Critical patent/EP3317584A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the present invention relates to high temperature components for use in high temperature environments such as gas turbines. More specifically, aspects of the present invention relate to hybrid components comprising a metal- reinforced ceramic matrix composite (CMC) material and methods for manufacturing the same.
  • CMC ceramic matrix composite
  • Gas turbines comprise a casing or cylinder for housing a compressor section, a combustion section, and a turbine section.
  • a supply of air is compressed in the compressor section and directed into the combustion section.
  • the compressed air enters a combustion inlet and is mixed with fuel.
  • the air/fuel mixture is then combusted to produce high temperature and high pressure gas. This working gas is then ejected past a combustor transition and travels into the turbine section of the turbine.
  • the turbine section comprises rows of vanes which direct the working gas to the airfoil portions of the turbine blades.
  • the gas causes the turbine blades to rotate, thereby turning the rotor.
  • the rotor is also attached to the compressor section, thereby turning the compressor and also an electrical generator for producing electricity.
  • Hot gas is then exhausted from the system. High efficiency may be achieved by heating the gas flowing through the combustion section to as high a temperature as is practical.
  • the hot gas may degrade various turbine components such as combustor components, transition ducts, vanes, ring segments, exhaust components, and turbine blades that the hot gas passes when flowing through the turbine.
  • CMC ceramic matrix composite
  • FIG. 1 is a perspective view of a component in accordance with an aspect of the present invention.
  • FIG. 2 is a perspective view of a component comprising a CMC body formed from stacked laminates in accordance with an aspect of the present invention.
  • FIG. 3 illustrates another embodiment of a metal skeleton structure in accordance with an aspect of the present invention.
  • FIG. 4 illustrates a CMC body being inserted within a metal skeleton structure in accordance with an aspect of the present invention.
  • FIG. 5 illustrates a CMC body comprising threaded ends structured to mate with fasteners in accordance with an aspect of the present invention.
  • FIG. 6 illustrates a CMC body having a thermal barrier coating about an exterior of the CMC body in accordance with an aspect of the present invention.
  • the component comprises a CMC material reinforced with a metal skeleton structure.
  • the CMC material of the component acts as a heat shield between the hot inner gas flowing through the turbine while the metal skeleton structure both supports the CMC material and carries structural loads to a greater extent than the CMC material.
  • the metal skeleton structure may further comprise any attachment(s) or interface(s) necessary for use of the device in a gas turbine. In this way, the attachment(s) or interface(s) for the metal-reinforced CMC components described herein may remain metal and nearly identical to current configurations where the component is formed solely from a superalloy, for example.
  • a hybrid component including a body comprising a ceramic matrix composite material and a metal skeleton structure encompassing at least a portion of the body.
  • the component further comprises a retaining structure carried by the metal skeleton structure effective to induce a compressive force on the body to limit movement of the body and the metal skeleton structure relative to one another and allow the metal skeleton structure to carry a greater amount of an external load than the body.
  • a method for forming a hybrid component comprises mating a body comprising a ceramic matrix composite material with a metal skeleton structure such that the metal skeleton structure encompasses at least a portion of the body.
  • the method comprises supplying a
  • an exemplary component 10 in accordance with an aspect of the present invention comprising a body 12 formed at least in part from a ceramic matrix composite (CMC) material 14.
  • the body 12 may define a cavity 15 therein.
  • the body portion 12 (hereinafter “CMC body 12") is at least partially encompassed about its exterior 16 by a metal skeleton structure 18.
  • a retaining structure 20 is provided which limits or prevents movement of the CMC body 12 relative to the metal skeleton structure 18, and vice-versa.
  • the retaining structure 20 is configured or structured such that it applies a compressive force to the CMC body 12 in order to maintain the CMC body 12 in a fixed position while also allowing the metal skeleton structure 18 to bear further structural loads for the component 10.
  • the CMC body 12 may be of any suitable size and dimension for its intended application.
  • the CMC body 12 is at least partially formed from the CMC material 14.
  • the CMC material 14 may include a ceramic matrix material that hosts a plurality of reinforcing fibers as is known in the art.
  • the CMC material 14 may be anisotropic, at least in the sense that it can have different strength characteristics in different directions. It is appreciated that various factors, including material selection and fiber orientation, can affect the strength characteristics of a CMC material.
  • the CMC material 14 may comprise oxide, as well as non-oxide CMC materials.
  • the CMC material 14 may comprise alumina
  • the fibers may comprise an aluminosilicate composition consisting of approximately 70% alumina; 28% silica; and 2% boron (sold under the name NEXTELTM 312).
  • the fibers may be provided in various forms, such as a woven fabric, blankets, unidirectional tapes, and mats. A variety of
  • CMC materials 14 for use herein are described in US Patent Nos. 8,058, 191 ; 7,745,022; 7, 153,096; 7,093,359; and 6,733,907, the entirety of each of which is hereby incorporated by reference.
  • the selection of materials is not the only factor which governs the properties of the CMC material 14 as the fiber direction may also influence the mechanical strength of the material, for example.
  • the fibers for the CMC material 14 may have any suitable orientation such as those described in U.S. Patent No. 7,153,096.
  • the CMC body 12 comprises a continuous solid body having as shown in FIG. 1 .
  • the body 12 may comprise a plurality of stacked laminate plates 22 formed from the CMC material 14.
  • each of the stacked laminate plates 22 may be cut to a desired shape via a laser cutting process and stacked to provide the desired body 12.
  • the stacked laminate plates 22 may be provided with a support structure, such as a tie rod, extending through the stacked laminates.
  • the plates may further include suitable structures, such as retainers, for radial compression of the plates. Exemplary processes for forming a body of stacked laminates from a CMC material and associated structures are set forth in U.S. Patent Nos.
  • Some advantages a stacked laminate structure include enabling CMC material to itself bear some structural loading via the individual plates, as well as increasing a number of possible dimensions and
  • the metal skeleton structure 18 may comprise any metal material which may provide an added strength to the body 12 and may carry an extent of loading on the component 10.
  • the metal material may comprise an alloy material such as a Fe-based alloy, a Ni-based alloy, a Co-based alloy as are well known in the art.
  • the alloy may comprise a superalloy.
  • superalloy may be understood to refer to a highly corrosion-resistant and oxidation-resistant alloy that exhibits excellent mechanical strength and resistance to creep even at high
  • Exemplary superalloy materials are commercially available and are sold under the trademarks and brand names Hastelloy, Inconel alloys (e.g., IN 738, IN 792, IN 939), Rene alloys (e.g. Rene N5, Rene 41 , Rene 80, Rene 108, Rene 142, Rene 220), Haynes alloys, Mar M, CM 247, CM 247 LC, C263, 718, X-750, ECY 768, 262, X45, PWA 1483 and CMSX (e.g.
  • CMSX-4) single crystal alloys GTD 1 1 1 , GTD 222, MGA 1400, MGA 2400, PSM 1 16, CMSX-8, CMSX-10, PWA 1484, IN 71 3C, Mar-M-200, PWA 1480, IN 100, IN 700, Udimet 600, Udimet 500 and titanium aluminide, for example.
  • the metal skeleton structure 18 may be formed from a metal material having a melting temperature of from 450-600° C due to the thermal protection provided by the CMC material 14.
  • the metal skeleton structure 18 may comprise any suitable
  • the metal skeleton structure 18 may be configured to extend from a base portion 24 of the CMC body 12 to a top portion 26 of the CMC body 12.
  • the metal skeleton structure 18 comprises a plurality of spaced apart ribs 28 that encompass and provide structural support to the body 12.
  • the ribs 28 may be of any suitable number, size, and shape to provide a desired degree of structural
  • the present invention is not limited to the embodiment of FIG. 1 and that the metal skeleton structure 18 may alternatively comprise any other suitable structure which encompasses at least a portion, if not all, of an exterior 1 6 of the CMC body 12 and which defines at least a plurality of openings 25 that allows at least a portion of the exterior 16 of the body 12 to remain exposed to the surrounding environment.
  • the metal skeleton structure 18 may alternatively comprise another structure such as a grid-like structure 30 as shown in FIG. 3 having a plurality of intersecting metal members 32 defining openings 34.
  • the exposure of the exterior 16 of the CMC body 12 may offer significant advantages, such as in an environment where the body 12 is exposed to a cooling air flow, such as circulating shell air.
  • a cooling air flow such as circulating shell air.
  • the CMC body 12 can be passively cooled and the amount of cooling air utilized for active cooling, which typically travels through or within the CMC body 12, may be reduced. This not only allows for material and cost savings, but allows for higher inlet temperatures which in turn may translate to greater performance and efficiency.
  • cooling air reduction in a combustion system can be either used to: 1 ) reduce primary zone temperature (PZT) for a constant rotor inlet temperature (RIT) operation case, thereby leading to reductions in NOx emissions; or 2) increase RIT (for a constant NOx case), thereby leading to increase in power output and combined cycle (CC) efficiency.
  • PZT primary zone temperature
  • RIT constant rotor inlet temperature
  • the metal skeleton structure 18 and the CMC body 12 comprise an interface which helps prevent rotation of the body 12 relative to the metal skeleton structure 18, or vice-versa.
  • the body 12 may comprise a plurality of channels 36, each channel 36 having a depth such that at least a portion of a respective rib 28 of a metal skeleton 18 may be received and disposed therein.
  • the ribs 28 of the metal skeleton 18 may be slidably inserted within the channels 36 to provide the desired interface between the CMC body 12 and the metal skeleton 18 for the component 10.
  • These channels 36 may also be provided in the stacked laminate structure of FIG. 2.
  • the ribs 28 of the metal support structure 18 may instead comprise channels 36 therein which are configured to receive corresponding portions of the CMC body 12 therein.
  • the retaining structure 20 may be any suitable structure for at least maintaining contact between the CMC body 12 and the metal skeleton 18.
  • the retaining structure 20 is further configured to induce a compressive force on the CMC body 12.
  • the metal skeleton structure 18 may be configured to receive an external load thereon instead of the structurally weaker CMC body 12.
  • the retaining structure 20 may comprise a retaining ring 38 which is configured to engage and fit over an exterior portion 39 the ribs 28 of the metal skeleton 18.
  • the retaining ring 20 may further include channels or clasps 40 as shown within which the ribs 28 may be engaged within or otherwise inserted.
  • the retaining ring 38 is shown as fitting over a topmost portion of the metal skeleton structure 18, it is understood that the present invention is not so limited. Further, the retaining ring 38 may comprise one or more additional retaining rings, or alternatively may comprise any other suitable structure.
  • the component 10 and/or retaining structure 20 may include any further structure(s) effective to at least assist in providing a compressive force on the CMC material 12.
  • a plurality of fasteners 42 may be provided which are configured to mate with threaded ends 44 on the ribs 28.
  • the retaining ring 38 is omitted from FIG. 5, but referring again to FIG. 1 , it can be appreciated that as fasteners 42 (such as nuts or bolts) are tightened, the fasteners 42 may increasingly cause the retaining ring 38 and/or metal skeleton structure 1 8 to place a greater compressive load or force on the CMC body 12.
  • This load or force not only maintains the CMC body 12 in a fixed position relative to the metal skeleton structure 18, but also forces the metal skeleton structure 18 to carry at least an amount of an external load upon a further application of an external load to the component 10.
  • the CMC body 12 may primarily carry thermal loads while the metal skeleton structure 18 may primarily carry structural loads upon use of the component in an environment exposing the component 10 to such loads, such as in a gas turbine environment.
  • the metal skeleton structure 18 may be fabricated so as to be formed with or otherwise may include any mating parts necessary for the component 10 to mate with another component.
  • the mating parts may be joined to the metal support structure 18 via any suitable method such as welding or soldering.
  • the component 10 may include a flange 44 on a base portion 24 thereof for attaching the component 10 to another component which is configured to mate with or receive the flange 44.
  • the component 1 0 may comprise a plurality of tabs 45 on a top portion 26 thereof for attachment of the component 10 to a combustor, for example.
  • the flange 44, tabs 45, or any other suitable mating structures are formed from metal.
  • the mating parts for the component 10 may remain metal and nearly identical to current configurations. As such, the components described herein can be easily incorporated into existing turbine systems.
  • a thermal barrier coating (TBC) 48 may be applied to an internal surface 50 of the CMC body 12 to prevent oxidation of or thermal damage to the CMC material since the internal surface 50 is exposed to high temperatures as shown in FIG. 6.
  • FIG. 6 is a cross-section taken at line A-A of FIG. 4.
  • the thermal barrier coating 48 may comprise a friable graded insulation (FG I) as is known in the art. See, for example, U.S. Patent Nos. 7,563,504; 7,198,462; 6,641 ,907; 6,676,783; and 6,235,370, each of which are incorporated by reference herein.
  • such thermal barrier coatings may instead or also be applied to an outer periphery of the CMC body 12.
  • a metal skeleton structure 18 as described herein may be first fabricated according to desired specifications, or otherwise provided from a commercial or suitable source.
  • the metal skeleton structure 18 may be cast or otherwise formed as a single piece, or may alternatively require joining of one of more of its components to remaining portions of the metal skeleton structure 18.
  • the CMC body 12 as described herein may be provided which may be configured for slidable insertion into the metal skeleton structure 18 via aligning the ribs 28 with channels 36 in the CMC body 12 and sliding the CMC body 12 therein in the direction of arrow B as shown.
  • the retaining structure 20 may be placed on an exterior of the metal skeleton structure 18 and the retaining structure 20 secured or otherwise tightened to prevent movement of the CMC body 12 relative to the metal skeleton structure 18.
  • clasps 40 carried by the retaining structure 20 may engage ribs 28 therein.
  • fasteners 42 may be tightened on threaded ends 44 of the ribs 28 such that the retaining structure 20 and/or metal skeleton structure 18 exerts a compressive load on the CMC body 12.
  • compressive load not only keeps the CMC body 12 in place, but also allows the metal skeleton structure 18 to bear further external loads.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un élément de matériau composite à matrice céramique (CMC) renforcé de métal hybride, ayant un corps (12) comprenant un matériau composite à matrice céramique (14) et une structure de squelette métallique (18) entourant au moins une partie du corps (12). Une structure de retenue (20) portée par la structure de squelette métallique (20) est en outre conçue pour induire une force de compression sur le corps (12) pour limiter un mouvement du corps (12) et de la structure de squelette métallique (18) l'un par rapport à l'autre, et permettre à la structure de squelette métallique (18) de porter une plus grande quantité de charge externe que le corps (12).
EP15832842.7A 2015-06-30 2015-06-30 Élément hybride comprenant un matériau composite à matrice céramique renforcé de métal Withdrawn EP3317584A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2015/038574 WO2017003458A1 (fr) 2015-06-30 2015-06-30 Élément hybride comprenant un matériau composite à matrice céramique renforcé de métal

Publications (1)

Publication Number Publication Date
EP3317584A1 true EP3317584A1 (fr) 2018-05-09

Family

ID=55315690

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15832842.7A Withdrawn EP3317584A1 (fr) 2015-06-30 2015-06-30 Élément hybride comprenant un matériau composite à matrice céramique renforcé de métal

Country Status (3)

Country Link
US (1) US20180292090A1 (fr)
EP (1) EP3317584A1 (fr)
WO (1) WO2017003458A1 (fr)

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US11143163B2 (en) * 2016-03-08 2021-10-12 Semtive Inc. Vertical axis wind turbine
US11187105B2 (en) * 2017-02-09 2021-11-30 General Electric Company Apparatus with thermal break
WO2020056133A1 (fr) 2018-09-12 2020-03-19 Ignacio Juarez Micro-onduleur et régulateur
US10890328B2 (en) * 2018-11-29 2021-01-12 DOOSAN Heavy Industries Construction Co., LTD Fin-pin flow guide for efficient transition piece cooling
US11506383B2 (en) * 2020-10-09 2022-11-22 Pratt & Whitney Canada Corp Combustor liner and method of operating same
CN117091158A (zh) 2022-05-13 2023-11-21 通用电气公司 燃烧器室网状结构
CN117091162A (zh) 2022-05-13 2023-11-21 通用电气公司 具有稀释孔结构的燃烧器
CN117091161A (zh) 2022-05-13 2023-11-21 通用电气公司 燃烧器衬里的中空板设计和结构
CN117091159A (zh) 2022-05-13 2023-11-21 通用电气公司 燃烧器衬里

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Also Published As

Publication number Publication date
US20180292090A1 (en) 2018-10-11
WO2017003458A1 (fr) 2017-01-05

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