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WO2019001788A1 - Composant cmc pour turbine comportant un revêtement barrière thermique, et procédé de fabrication associé - Google Patents

Composant cmc pour turbine comportant un revêtement barrière thermique, et procédé de fabrication associé Download PDF

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Publication number
WO2019001788A1
WO2019001788A1 PCT/EP2018/059154 EP2018059154W WO2019001788A1 WO 2019001788 A1 WO2019001788 A1 WO 2019001788A1 EP 2018059154 W EP2018059154 W EP 2018059154W WO 2019001788 A1 WO2019001788 A1 WO 2019001788A1
Authority
WO
WIPO (PCT)
Prior art keywords
cmc
turbine component
layer
strength additive
present
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.)
Ceased
Application number
PCT/EP2018/059154
Other languages
German (de)
English (en)
Inventor
Stefan Lampenscherf
Gia Khanh Pham
Niels Van Der Laag
Steffen Walter
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 AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 AG, Siemens Corp filed Critical Siemens AG
Publication of WO2019001788A1 publication Critical patent/WO2019001788A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
    • C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
    • C04B35/565—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide
    • C—CHEMISTRY; METALLURGY
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    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/71—Ceramic products containing macroscopic reinforcing agents
    • C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
    • C04B35/80—Fibres, filaments, whiskers, platelets, or the like
    • C—CHEMISTRY; METALLURGY
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    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
    • C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
    • C04B41/5025—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials with ceramic materials
    • C04B41/5042—Zirconium oxides or zirconates; Hafnium oxides or hafnates
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
    • C04B41/81—Coating or impregnation
    • C04B41/85—Coating or impregnation with inorganic materials
    • C04B41/87—Ceramics
    • 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
    • F01D5/288—Protective coatings for blades
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    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
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    • C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
    • C04B2235/3205—Alkaline earth oxides or oxide forming salts thereof, e.g. beryllium oxide
    • C04B2235/3206—Magnesium oxides or oxide-forming salts thereof
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    • C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
    • C04B2235/3217—Aluminum oxide or oxide forming salts thereof, e.g. bauxite, alpha-alumina
    • C04B2235/3222—Aluminates other than alumino-silicates, e.g. spinel (MgAl2O4)
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    • C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
    • C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
    • C04B2235/3225—Yttrium oxide or oxide-forming salts thereof
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    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/30—Constituents and secondary phases not being of a fibrous nature
    • C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
    • C04B2235/3231—Refractory metal oxides, their mixed metal oxides, or oxide-forming salts thereof
    • C04B2235/3244—Zirconium oxides, zirconates, hafnium oxides, hafnates, or oxide-forming salts thereof
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    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
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    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/30—Constituents and secondary phases not being of a fibrous nature
    • C04B2235/34—Non-metal oxides, non-metal mixed oxides, or salts thereof that form the non-metal oxides upon heating, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
    • C04B2235/3418—Silicon oxide, silicic acids or oxide forming salts thereof, e.g. silica sol, fused silica, silica fume, cristobalite, quartz or flint
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    • C04B2235/52—Constituents or additives characterised by their shapes
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    • C04B2235/5216—Inorganic
    • C04B2235/522—Oxidic
    • C04B2235/5224—Alumina or aluminates
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    • C04B2235/522—Oxidic
    • C04B2235/5228—Silica and alumina, including aluminosilicates, e.g. mullite
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    • C04B2235/54—Particle size related information
    • C04B2235/5418—Particle size related information expressed by the size of the particles or aggregates thereof
    • C04B2235/5436—Particle size related information expressed by the size of the particles or aggregates thereof micrometer sized, i.e. from 1 to 100 micron
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    • C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
    • C04B2235/616—Liquid infiltration of green bodies or pre-forms
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
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    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/34—Oxidic
    • C—CHEMISTRY; METALLURGY
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    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
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    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C04B2237/365—Silicon carbide
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    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/609—Grain size

Definitions

  • the invention relates to turbine components and / or gas turbine elements in which - at least partially - the herkömmli ⁇ chen superalloys by CMCs Ceramic Matrix Composites - are replaced.
  • the invention relates to the adhesion of the coatings applied to the CMCs, in particular thermal protection.
  • the cooling air is used to provide structural stability of the hot ⁇ SEN gas directly come into connection components to warranty.
  • CMCs in particular fiber-reinforced CMCs
  • fiber-reinforced CMCs is an alternative and can be used alone or in combination Combination with superalloys are used to create novel turbine components.
  • the oxide CMCs that is to say the metal oxide-based CMC materials, exhibit increased resistance to, for example, oxidation.
  • the object of the present invention is therefore to provide a CMC turbine component or CMC-metal hybrid turbine component with a coating on the CMC as protection against the damage caused by hot gas flow damage to turbine components, in particular gas turbine components, which adheres well and / or a high breaking strength to avoid spallation damage in the coating and / or the surface of the CMC shows.
  • a thermal barrier coating is the subject of the present invention ei ⁇ ne CMC turbine component or CMC-metal hybrid turbine component, to- at least on a CMC surface through a
  • Is producible lamination comprising, at least in a surface-near position of CMC laminate one or more breaking strength Additi (s) are provided, ie, a chemical and / or physical barrier against crack ⁇ formation, crack expansion and / or cracking within these CMC-able form.
  • the subject of the invention is a method for producing a CMC turbine component or a CMC-metal hybrid turbine component with a thermal
  • thermal barrier layer in particular ⁇ by Atmospheric Plasma Spraying, APS.
  • Atoms and / or groups of atoms which belong to chemical elements other than the matrix of the CMC material and / or the reinforcing fiber (s) of the CMC layer and optionally interfere, repel or attract, in particular sterically, and / or
  • CMC layers in the form of prepregs are produced in a first step. These are either fibers, fiber fabrics and / or fiber composites which are infiltrated and / or impregnated with ceramic matrix and deposited on press molds, such as press cores, laid down in layers, ie laminated.
  • press molds such as press cores, laid down in layers, ie laminated.
  • the ceramic matrix hereinafter referred to as "slurry,”
  • the additives referred to herein as "break strength additives" interactions ⁇ ken comprises according to the prior art, a number of additives, the presence of which is not affected by the subject matter of the present invention. Preferably With these additives, little or no, they neither replace the conventional additives, nor do they usually require a change in the use of conventional additives commonly used in the manufacture of laminate prepregs.
  • a CMC laminate is a stack of a plurality of CMC layers of impregnated fibers, fiber fabrics and / or fiber composites, which is sintered to produce a CMC turbine component.
  • at least the uppermost CMC layer of the CMC laminate generally forms the surface of the finally sintered CMC laminate, which is roughened to apply a thermal barrier layer, for example via atmospheric plasma spraying.
  • a CMC layer typically comprises a ceramic matrix in which fibers, present as a single fiber and / or braided fiber, fiber fabric and / or fiber composites thereof gene ⁇ vorlie. For example, it is based on silicon carbide ceramic or so-called oxide ceramic based matrix and / or fiber materials.
  • oxide-ceramic-based matrix materials oxide-ceramic-based fibers, fiber fabrics and / or fiber composites are also used.
  • Their materials are for example selected from the group of the following materials:
  • Zirconia doping in the range of 5 to 30 mol%, especially 10 mol% to 25 mol%, and more preferably 15 mol% zirconia in alumina is a preferred fiber material.
  • All of the aforementioned fiber materials may be in a fiber, a fiber fabric and / or in a fiber as used in the present composite, alone or in arbitrary combination be ⁇ such as alumina as mullite fiber are present.
  • ⁇ such as alumina as mullite fiber are present.
  • a slurry is used, in which the ceramic matrix material is a liquid to viscous before ⁇ , so that the fiber, the fiber composite and / or the fiber web may be impregnated with the slurry and with the fiber, the fiber web and / or the fiber composite together forms the CMC prepreg layer.
  • the breaking strength additive s acting as an obstacle to cracking, crack expansion and / or fracturing incorporated ,
  • protruding slips are ent ⁇ removed on the surface of the CMC prepreg laminate and by slip, in which one or more breaking strength additive (s), acting as an obstacle against Rissbil ⁇ extension, crack expansion and / or fracturingLear- beitet are to be replaced.
  • breaking strength additive s
  • the surface has a slip to which one or more breaking strength additive (s) are added that act as a barrier to crack formation, crack expansion and / or cracking, is then ge for CMC laminate sinters ⁇ .
  • breaking strength additive s
  • a thermal barrier layer for example a TBC, which again is, for example, yttrium-stabilized zirconium (YSZ) -based, the prior art activates the surface of the CMC layer so that the thermal barrier layer is thereon better liable.
  • the surface of a CMC layer is basically a bit too soft to ensure good adhesion of a sprayed thermal barrier layer.
  • breaking strength additives can be used alone and / or turned ⁇ ⁇ works in be arbitrary combinations in the affected prepreg layer are present.
  • the breaking strength additive (s) may be present as particles in any form.
  • fracture toughness additive particles may be spherical, rod-shaped and / or platelet-shaped. Regardless, the fracture toughness additive (s), as powders of irregularly shaped grains and / or crystallites, and / or any combination of the foregoing
  • the breaking strength additives can be in the form of larger particles whose mean particle size beispielswei ⁇ se by 10 to 20 times greater than that, for example, present in the matrix grains be and / or, for example, present in the fibers crystallites.
  • CMC Bruchfestig ⁇ keits additives having a particle size in the range of 10 ym to lOOym, preferably ym in the range of 15 to 70 ym and more preferably ym to 50 ym, are present in the range of 22nd
  • An ultimate strength additive according to the present invention may be crystalline, semi-crystalline and / or powder.
  • the one or more rupture strength additive (s) are beispielswei ⁇ se in an amount of up to 50% by weight, thus for example in the range of 1 wt% to 50 wt%, particularly from 5 wt% to 20 wt%, based on the unsintered Sludge mass - before.
  • Barrier layer such as an APS-TBC application, and it has been demonstrated that significantly less damage caused by fiber breakage during laser treatment and / or by sand blasting, as compared to the same ready-sintered CMC laminates without breaking strength additives.
  • the invention discloses for the first time a technique by which a conventional simple APS application of a thermal
  • Barrier layer on a CMC turbine component surface is made possible.
  • one or more breaking strength additives are incorporated into the CMC surface, which form a chemical and / or physical barrier against

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Inorganic Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un composant CMC pour turbine, comprenant un matériau CMC à base d'oxydes métalliques ou de carbure de silicium, comportant un revêtement barrière thermique au moins sur une surface de CMC qui peut être fabriquée par un procédé de contre-collage ; au moins dans une couche proche de la surface du stratifié de CMC, un ou plusieurs additifs de résistance à la rupture sont prévus, qui sont choisis dans le groupe constitué par les composés suivants : dioxyde de zirconium - ZrO2 -, dioxyde de silicium - SiO2 -, dioxyde de magnésium - MgO2 -, grenat d'yttrium et d'aluminium - YAG – et/ou oxyde d'yttrium Y2O3, qui forment un empêchement chimique et/ou physique à la fissuration, à la propagation des fissures et/ou à la formation d'une rupture à l'intérieur de cette couche de CMC, l'additif de résistance à la rupture étant présent en une quantité de 1 à 50 % en poids, par rapport à la couche de préimprégné de CMC non frittée. L'invention décrit pour la première fois une technique grâce à laquelle une application simple et classique par APS permet d'avoir une couche-barrière thermique sur une surface d'un composant CMC pour turbine.
PCT/EP2018/059154 2017-06-27 2018-04-10 Composant cmc pour turbine comportant un revêtement barrière thermique, et procédé de fabrication associé Ceased WO2019001788A1 (fr)

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DE102017210819.3A DE102017210819A1 (de) 2017-06-27 2017-06-27 CMC-Turbinenkomponente mit thermischer Barriere-Beschichtung, sowie Herstellungsverfahren dazu
DE102017210819.3 2017-06-27

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Cited By (1)

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WO2019185246A1 (fr) * 2018-03-26 2019-10-03 Siemens Aktiengesellschaft Pièce moulée en céramique composite renforcée de fibres oxydée, ainsi que procédé pour la fabrication d'une pièce moulée et dispositif pour l'exécution de ce procédé

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DE102017222489A1 (de) 2017-12-12 2019-06-13 Siemens Aktiengesellschaft CMC-Formkörper mit neuer Oberfläche, sowie Herstellungsverfahren dazu

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US6497776B1 (en) * 1998-12-18 2002-12-24 Rolls-Royce Plc Method of manufacturing a ceramic matrix composite
CA2974485A1 (fr) * 2014-12-12 2016-06-16 Kyoto University Materiau composite en carbure de silicium renforce par des fibres de carbure de silicium
WO2016133990A1 (fr) * 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Composant de turbine composite à matrice en céramique avec caractéristiques de surface techniques conservant un revêtement formant barrière thermique

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US20160153288A1 (en) * 2013-03-15 2016-06-02 General Electric Company Recession resistant ceramic matrix composites and environmental barrier coatings
US10494310B2 (en) * 2015-09-14 2019-12-03 Rolls-Royce Corporation Dense environmental barrier coatings
EP3241817B1 (fr) * 2016-05-02 2021-01-27 Rolls-Royce High Temperature Composites Inc Formation d'une couche de surface sur un article composite à matrice céramique

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Publication number Priority date Publication date Assignee Title
US6497776B1 (en) * 1998-12-18 2002-12-24 Rolls-Royce Plc Method of manufacturing a ceramic matrix composite
CA2974485A1 (fr) * 2014-12-12 2016-06-16 Kyoto University Materiau composite en carbure de silicium renforce par des fibres de carbure de silicium
WO2016133990A1 (fr) * 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Composant de turbine composite à matrice en céramique avec caractéristiques de surface techniques conservant un revêtement formant barrière thermique

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019185246A1 (fr) * 2018-03-26 2019-10-03 Siemens Aktiengesellschaft Pièce moulée en céramique composite renforcée de fibres oxydée, ainsi que procédé pour la fabrication d'une pièce moulée et dispositif pour l'exécution de ce procédé

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