US20130184141A1 - Process for producing ceramic fiber-reinforced composite material and ceramic fiber-reinforced composite material - Google Patents

Process for producing ceramic fiber-reinforced composite material and ceramic fiber-reinforced composite material Download PDF

Info

Publication number
US20130184141A1
US20130184141A1 US13/743,293 US201313743293A US2013184141A1 US 20130184141 A1 US20130184141 A1 US 20130184141A1 US 201313743293 A US201313743293 A US 201313743293A US 2013184141 A1 US2013184141 A1 US 2013184141A1
Authority
US
United States
Prior art keywords
composite material
reinforced composite
silicon
ceramic fiber
infiltrating
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
Application number
US13/743,293
Other languages
English (en)
Inventor
Toshio Ogasawara
Takuya Aoki
Masaki Kotani
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.)
Japan Aerospace Exploration Agency JAXA
Original Assignee
Japan Aerospace Exploration Agency JAXA
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 Japan Aerospace Exploration Agency JAXA filed Critical Japan Aerospace Exploration Agency JAXA
Assigned to JAPAN AEROSPACE EXPLORATION AGENCY reassignment JAPAN AEROSPACE EXPLORATION AGENCY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: AOKI, TAKUYA, KOTANI, MASAKI, OGASAWARA, TOSHIO
Publication of US20130184141A1 publication Critical patent/US20130184141A1/en
Priority to US15/016,195 priority Critical patent/US10597333B2/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • 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
    • C04B35/71—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
    • 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
    • C04B35/58—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 borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides
    • C04B35/58085—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 borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides based on silicides
    • C04B35/58092—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 borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides based on silicides based on refractory metal silicides
    • 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
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62844—Coating fibres
    • C04B35/62857—Coating fibres with non-oxide ceramics
    • C04B35/6286—Carbides
    • C04B35/62863—Silicon carbide
    • 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
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62844—Coating fibres
    • C04B35/62857—Coating fibres with non-oxide ceramics
    • C04B35/62873—Carbon
    • 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
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62884—Coating the powders or the macroscopic reinforcing agents by gas phase techniques
    • 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
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62894—Coating the powders or the macroscopic reinforcing agents with more than one coating layer
    • 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
    • C04B41/009—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
    • C04B41/5093—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 elements other than metals or carbon
    • C04B41/5096—Silicon
    • 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
    • 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
    • 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
    • C04B2235/38—Non-oxide ceramic constituents or additives
    • C04B2235/3817—Carbides
    • C04B2235/3826—Silicon carbides
    • 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
    • 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
    • C04B2235/38—Non-oxide ceramic constituents or additives
    • C04B2235/3891—Silicides, e.g. molybdenum disilicide, iron silicide
    • 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
    • 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
    • C04B2235/42—Non metallic elements added as constituents or additives, e.g. sulfur, phosphor, selenium or tellurium
    • C04B2235/422—Carbon
    • C04B2235/424—Carbon black
    • 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
    • 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
    • C04B2235/42—Non metallic elements added as constituents or additives, e.g. sulfur, phosphor, selenium or tellurium
    • C04B2235/428—Silicon
    • 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
    • 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
    • C04B2235/48—Organic compounds becoming part of a ceramic after heat treatment, e.g. carbonising phenol resins
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
    • C04B2235/608—Green bodies or pre-forms with well-defined density
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
    • C04B2235/614—Gas infiltration of green bodies or pre-forms
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • 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
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
    • C04B2235/80—Phases present in the sintered or melt-cast ceramic products other than the main phase
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
    • C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
    • C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
    • C04B2235/9669—Resistance against chemicals, e.g. against molten glass or molten salts
    • C04B2235/9684—Oxidation resistance
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/14—Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
    • 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]

Definitions

  • the present invention relates to a process for producing a ceramic fiber-reinforced composite material that is formed by infiltrating the entirety or a part of pores that are present in a composite material substrate obtained by forming ceramic fibers into a composite with a matrix (base material) formed of an inorganic substance, with an infiltrating material, and can be used at a high temperature, and to a ceramic fiber-reinforced composite material.
  • a special interface layer is required for an interface between ceramic fibers and a matrix so as to control the adhesion strength between the ceramic fibers and matrix, and interface layers of hexagonal boron nitride (h-BN) or carbon (c) are most frequently used.
  • h-BN hexagonal boron nitride
  • c carbon
  • oxidation by water vapor in a temperature range of 800 to 1,000° C. generates in boron nitride and oxidation by air in a temperature range of 800° C. or more generates in carbon, to thereby inhibit the high temperature properties of the ceramic fiber-reinforced composite material.
  • CVD chemical vapor deposition process
  • CVI chemical vapor infiltration process
  • PIP ceramic precursor infiltration-pyrolysis process
  • RS reactive sintering process
  • JP-A Japanese Patent Application Laid-Open
  • the technique known in the above-mentioned JP-A No. 10-259070 has a problem that, since the glass is chemically unstable in a temperature range of 1,000° C. or more, the material is deteriorated over time by use in that temperature range and thus has low durability.
  • the technique also has a problem that the material cannot be applied in a high temperature range over 1,300° C. since melting and vaporization of the glass generate.
  • melt infiltration of silicon it is necessary to heat to a temperature equal to or more than 1,414° C. that is the melting point of silicon, generally to 1450° C. or more, but there is a problem that heat decomposition occurs in this temperature range in many ceramic fibers, and thus the strength of the ceramic fibers is significantly decreased.
  • amorphous silicon carbide (SiC) fibers, amorphous alumina fibers or the like, which are generally used as ceramic fibers is conducted at a temperature equal to or more than the production temperature of these ceramic fibers, heat decomposition proceeds and the mechanistic properties are significantly inhibited.
  • the technique known in the above-mentioned JP-A No. 10-167831 has a problem that the strength property of the composite material significantly decreases in a temperature range over 1,300° C. since the strength property significantly depends on the metallic silicon as a binder.
  • the present invention aims at providing a ceramic fiber-reinforced composite material obtained by forming ceramic fibers into a composite with a matrix formed of an inorganic substance, which suppresses the deterioration of an interface layer, improves mechanistic properties and has excellent durability even under a high temperature, even general ceramic fibers are used, without complicating the production steps.
  • a first aspect of the invention solves the above-mentioned problem by providing a process for producing a ceramic fiber-reinforced composite material that is formed by infiltrating the entirety or apart of pores that are present in a composite material substrate obtained by forming ceramic fibers into a composite with a matrix formed of an inorganic substance, with an infiltrating material, wherein the infiltrating material is an alloy having a composition that is constituted by a disilicate of at least one or more transition metal among transition metals selected from scandium, yttrium, titanium, zirconium, hafnium, vanadium, niobium and tantalum belonging to Group 3A, Group 4A or Group 5A of the Periodic Table and silicon as the remainder, has a silicon content ratio (including the silicon in the transition metal disilicate) of 66.7 at % or more, and gives a melting point that is lower than that of a single body of silicon, and the process comprises melt-infiltrating the pores that are present in the composite material substrate with the in
  • a second aspect of the invention solves the above-mentioned problem by providing the entirety or a part of the pores that are present in the composite material substrate with free carbon prior to the melt infiltration, and reacting the alloy as the infiltrating material and the free carbon in the pores during the melt infiltration to generate silicon carbide and a carbide of the transition metal, besides the constitution of the process for producing a ceramic fiber-reinforced composite material of the first aspect.
  • Third and fourth aspects of the invention solve the above-mentioned problem by that the melting point of the residual alloy that is solidified in the pores after the melt infiltration is higher than the melting point of the alloy as the infiltrating material prior to the melt infiltration, besides the constitutions of the processes for producing a ceramic fiber-reinforced composite material of the first and second aspects.
  • a ninth aspect of the invention solves the above-mentioned problem by providing a ceramic fiber-reinforced composite material that is formed by infiltrating the entirety or a part of pores that are present in a composite material substrate obtained by forming ceramic fibers into a composite with a matrix formed of an inorganic substance, with an infiltrating material, wherein the infiltrating material is an alloy having a composition that is constituted by a disilicate of at least one or more transition metal among transition metals selected from scandium, yttrium, titanium, zirconium, hafnium, vanadium, niobium and tantalum belonging to Group 3A, Group 4A or Group 5A of the Periodic Table and silicon as the remainder, has a silicon content ratio (including the silicon in the transition metal disilicate) of 66.7 at % or more, and gives a melting point that is lower than that of a single body of silicon.
  • a tenth aspect of the invention solves the above-mentioned problem by that silicon carbide and a carbide of the transition metal are present in interface regions between the pores and the infiltrating material, besides the constitution of the ceramic fiber-reinforced composite material of the ninth aspect.
  • Eleventh and twelfth aspects of the invention solve the above-mentioned problem by that the melting point of the residual alloy that is solidified in the pores after the melt infiltration is higher than the melting point of the alloy as the infiltrating material prior to the melt infiltration, besides the constitutions of the ceramic fiber-reinforced composite materials of the ninth and tenth aspects.
  • the above-mentioned ceramic fibers are silicon carbide fibers, besides the constitutions of the ceramic fiber-reinforced composite materials of the ninth, tenth, eleventh and twelfth aspects.
  • the melting point of the alloy as the infiltrating material becomes lower than 1,414° C. that is the melting point of silicon, by adjusting the silicon content ratio (including the silicon in the transition metal disilicate) of the alloy to 66.7 at % or more, thereby the temperature of the alloy as the infiltrating material during the melt infiltration can be suppressed to be low during the melt infiltration treatment of the infiltrating material.
  • the alloy as the infiltrating material has a property that the melting point of the alloy simply decreases from 1,414° C. that is the melting point of silicon as the silicon content ratio decreases from 100 at %, and becomes the lowest at 85 to 95 at %, and the melting point simply increases in the range of 66.7 at % or more as the content ratio further decreases, and the melting points of the alloy are relatively linear at the both sides of the lowest point and do not have extreme flexion point and singular point. Therefore, the melting point of the alloy during the melt infiltration treatment can be stably retained in a region lower than the melting point of silicon.
  • the ceramic fibers into a composite with a matrix formed of an inorganic substance in the step prior to the melt infiltration of the infiltrating material, the effect of the direct contact of the alloy as the molten infiltrating material with the ceramic fibers and interface layer can be completely prevented.
  • the treatment is a sealing treatment on the pores that are present in the composite material substrate, heat treatment distortion of the ceramic fibers which accompanies the melt infiltration of the alloy as the infiltrating material generates significantly little, and thus the obtained ceramic fiber-reinforced composite material has a high dimensional accuracy.
  • the pores that are present in the composite material substrate are sealed by the silicon alloy as the infiltrating material, and the like, and thus entry of gases (air and water vapor) that oxidize the interface layer of the composite material substrate, thereby the oxidation resistance at the interface is significantly improved.
  • the carbides function as a reaction protective layer for the interface region to thereby suppress the deterioration of the interface layer and improve the mechanistic properties of the ceramic fiber-reinforced composite material.
  • the silicon carbide and carbide of the transition metal are generated, the amount of the residual alloy that remains after the solidification is decreased, and thus the mechanistic properties can be improved.
  • the constitutions of the third, fourth, eleventh and twelfth aspects it becomes possible to accommodate up to the heat resistance limit of the composite material substrate itself without being affected by the melting point of the residual alloy that remains after the solidification in the practical use of the ceramic fiber-reinforced composite material, by increasing the melting point of the residual alloy that remains after the solidification by changing the ratio of the silicon and other transition metal in the residual alloy.
  • the interface regions between the pores in the composite material substrate and the infiltrating material are reinforced more, thereby the deterioration of the interface layer is suppressed more and the mechanistic properties of the ceramic fiber-reinforced composite material are improved more.
  • FIG. 1 is the phase diagram (schematic view) of an exemplary embodiment of the alloy as the infiltrating material used in the present invention.
  • FIG. 2 is the micrograph of the cross-sectional surface of the ceramic fiber-reinforced composite material of the present invention.
  • the specific embodiment of the process for producing a ceramic fiber-reinforced composite material of the present invention may be any one as long as it is a process for producing a ceramic fiber-reinforced composite material that is formed by infiltrating the entirety or a part of pores that are present in a composite material substrate obtained by forming ceramic fibers into a composite with a matrix formed of an inorganic substance, with an infiltrating material, wherein the infiltrating material is an alloy having a composition that is constituted by a disilicate of at least one or more transition metal among transition metals selected from scandium, yttrium, titanium, zirconium, hafnium, vanadium, niobium and tantalum belonging to Group 3A, Group 4A or Group 5A of the Periodic Table and silicon as the remainder, has a silicon content ratio (including the silicon in the transition metal disilicate) of 66.7 at % or more, and gives a melting point that is lower than that of a single body of silicon, and the process includes melt-in
  • the specific embodiment of the ceramic fiber-reinforced composite material of the present invention may be any one as long as it is a ceramic fiber-reinforced composite material that is formed by infiltrating the entirety or a part of pores that are present in a composite material substrate obtained by forming ceramic fibers into a composite with a matrix formed of an inorganic substance, with an infiltrating material, wherein the infiltrating material is an alloy having a composition that is constituted by a disilicate of at least one or more transition metal among transition metals selected from scandium, yttrium, titanium, zirconium, hafnium, vanadium, niobium and tantalum belonging to Group 3A, Group 4A or Group 5A of the Periodic Table and silicon as the remainder, has a silicon content ratio (including the silicon in the transition metal disilicate) of 66.7 at % or more, and gives a melting point that is lower than that of a single body of silicon.
  • the ceramic fiber-reinforced composite material according to the present invention is obtained by pre-forming a composite material base material obtained by forming ceramic fibers as reinforcing fibers into a composite with an oxide or an inorganic substance such as carbon as a matrix (base material), and melt-infiltrating pores or voids that remain in the composite material substrate with a transition metal disilicate/silicon alloy as the infiltrating material.
  • the composite material substrate is preformed by forming a preform of ceramic fibers into a composite with an inorganic material as a matrix (base material) by a chemical vapor deposition process (CVD), a chemical vapor infiltration process (CVI), a ceramic precursor infiltration-pyrolysis process (PIP), a reactive sintering process (RS) or the like.
  • CVD chemical vapor deposition process
  • CVI chemical vapor infiltration process
  • PIP ceramic precursor infiltration-pyrolysis process
  • RS reactive sintering process
  • carbon, a nitride, a carbide, an oxide, a phosphate, a boride, crystallized glass or the like can be applied.
  • the ceramic fibers can be applied to either long fibers or short fibers, and as reinforced forms of the preforms thereof, various states of arrangement such as unidirectional reinforcement, woven fabric lamination, three-dimensional woven fabric and woven fabric lamination/suturation can be applied.
  • FIG. 1 A schematic drawing of a representative phase diagram of the transition metal disilicate/silicon alloy as the infiltrating material is shown in FIG. 1 .
  • T mp1 is the temperature at which the melting point of the silicon alloy is the lowest
  • T mp2 is the melting point of the transition metal disilicate
  • a predetermined component ratio within the composition range A is used as the composition of the transition metal disilicate/silicon alloy in the present invention.
  • transition metal disilicate/silicon alloys have significant features that the transition metal disilicates have melting points (T mp2 ) that are higher than the melting point of silicon (1,414° C.), the transition metal disilicate/silicon alloys have melting points that are lower than the melting point of silicon (1,414° C.), and the like.
  • an alloy having a low lowest melting point and containing a transition metal disilicate having a high melting point is desirable, and it is found that titanium, zirconium and hafnium, which are transition metals in Group 4A of the Periodic Table, are preferable.
  • the transition metal disilicate In vanadium, niobium and tantalum, which are transition metals in Group 5A of the Periodic Table, the transition metal disilicate has a high melting point, whereas the transition metal disilicate/silicon alloy has a slightly high melting point. Conversely, in the cases of scandium and yttrium, which are transition metals in Group 3A of the Periodic Table, the transition metal disilicate/silicon alloy has a low melting point, whereas the transition metal disilicate tends to show a slightly low melting point.
  • hafnium, zirconium and yttrium can be preferably used as the transition metal disilicate/silicon alloy for infiltration since the transition metal disilicate/silicon alloy has a low melting point, the transition metal disilicate has a high melting point, and the transition metal disilicate has relatively excellent oxidation resistance.
  • the melting point is decreased to about 1,330° C. at the lowest, and thus it becomes possible to decrease the melt infiltration temperature to about 1,380° C.
  • the silicon in the alloy reacts with the free carbon present in the pores to generate silicon carbide, whereas the reaction amounts of the hafnium and free carbon in the alloy is relatively small, and thus the amount of the hafnium in the hafnium disilicate/silicon alloy changes little.
  • the silicon on the hafnium disilicate/silicon alloy decreases, and the melting point in the hafnium disilicate/silicon alloy consequently increases according to the phase diagram shown in FIG. 1 .
  • the melting point of the residual hafnium disilicate/silicon alloy after the infiltration close to the melting point (T mp2 ) of hafnium disilicate by suitably adjusting the amount of the free carbon, the infiltration temperature and the infiltration time, and the melting point of the residual hafnium disilicate/silicon alloy can be increased to about 1,400° C. that is the melting point of silicon.
  • amorphous silicon carbide fibers formed of a chemical composition of Si—Zr—C—O (Tyrrano ZMI fiber (trade name: Ube Industries, Ltd.) which had been woven into an orthogonal three-dimensional woven fabric having a shape of about 120 mm ⁇ 120 mm ⁇ 4 mm was used as a preform.
  • the fiber volume fractions of the woven fabric are 20%, 20% and 0.3%, respectively, in the X, Y and Z directions.
  • a carbon layer having a thickness of about 0.1 to 0.3 ⁇ m was first formed on the fiber surface on the preform of the amorphous silicon carbide fibers by a chemical vapor deposition process (CVI process) using propane (C 3 H 8 ).
  • SiC having a thickness of 5 to 10 ⁇ m was deposited on the fiber surface by a CVI process using silicon tetrachloride (SiCl 4 ) and propane (C 3 H 8 ) to form a matrix, to thereby form a composite material substrate that is a premolded product.
  • the composite material substrate has a bulk density of about 1.8 g/cc and a pore rate of about 25%.
  • the composite material substrate that had been pre-formed in this way was cut into about a width of 30 mm ⁇ a thickness of 4 mm ⁇ a length 50 mm and used as a sample, and the powders of the transition metal disilicate/silicon alloys having the respective composition shown in Examples 1 to 6 in the following Table 2 were each applied thereto by using a spray glue (Spray Glue 77 (trade name: manufactured by 3M)).
  • the powder was applied five times to every surface of the sample, and the sample to which the transition metal disilicate/silicon alloy had been applied was put into a carbon crucible and heated in vacuum by using a carbon heater furnace to infiltrate the pores in the composite material substrate with the transition metal disilicate/silicon alloy to give a ceramic fiber-reinforced composite material (Examples 1 to 6).
  • the temperatures for the infiltration treatment were each preset to a temperature that is about 50° C. higher than the melting point, as shown in the following Table 2, and the heat treatment time was 1 hour.
  • Comparative Example 1 an example in which the infiltration treatment with the infiltrating material was not conducted (Comparative Example 1), an example in which silicon was melt-infiltrated in vacuum at 1,430° C. (Comparative Example 2), and an example in which silicon was melt-infiltrated in vacuum at 1,470° C. (Comparative Example 3) were defined as comparative examples.
  • a bending test piece of 4 ⁇ 4 ⁇ length 50 mm was processed from each ceramic fiber-reinforced composite material, and bending tests and measurements of pore rates at 1,200° C. and 1,300° C. under room temperature in argon were conducted.
  • the measurement conditions were an airflow amount of 100 mL/min and a temperature raising velocity of 10° C./min, and the temperature was retained at 1,200° C. for 5 hours and the change in the weight during that time (increase in amount by oxidation) was measured.
  • the pore rate was 4% or less at the most and thus the infiltration property was extremely fine. Specifically, it is understood that, in the cases of the transition metal disilicate/silicon alloys containing hafnium and yttrium, respectively, the increase in amount by oxidation at 1,200° C. is also decreased, and thus materials also having excellent oxidation resistance can be obtained.
  • Example 7 in the present invention a pre-formed composite material substrate as in the above-mentioned Examples 1 to 6 was subjected to a vacuum infiltration treatment and a dry-curing treatment at 120° C., by using an aqueous solution containing 19.2 wt % of carbon black had been dispersed therein (Aqua-Black 162 (trade name: Tokai Carbon Co., Ltd.)) to which 0.5 wt % of an acrylic resin-based binder (Merposol (trade name: Matsumoto Yushi-Seiyaku Co., Ltd.) had been added.
  • FIG. 2 is the micrograph of the cross-sectional surface of the obtained ceramic fiber-reinforced composite material.
  • Example 8 in the present invention a pre-formed composite material substrate as in the above-mentioned Examples 1 to 6 was soaked in a solution obtained by diluting a novolak-type phenol resin (J-325 (trade name: DIC Corporation)) with a solvent (methyl alcohol) at a ratio of 1:1, vacuum deaeration for about 24 hours was conducted to infiltrate the pores with the phenol resin, the solvent was removed in a vacuum drier at 100° C. for 5 hours, and the phenol resin was cured in the air at 160° C.
  • a novolak-type phenol resin J-325 (trade name: DIC Corporation)
  • solvent methyl alcohol
  • Example 8 a ceramic fiber-reinforced composite material having an excellent bending strength and contains a small amount of the residual hafnium disilicate/silicon alloy could be obtained as in Example 7.
  • the ceramic fiber-reinforced composite material of the present invention can prevent the alloy as the infiltrating material, and the like from melting at a high temperature and partially scattering to thereby inhibit the oxidation resistance, and thus is preferable for, for example, movable parts that are used under high temperatures such as moving blades in gas turbines, and also exerts excellent performances in any use such as improvement of bending strength and improvement of anticorrosive property.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Ceramic Products (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
US13/743,293 2012-01-18 2013-01-16 Process for producing ceramic fiber-reinforced composite material and ceramic fiber-reinforced composite material Abandoned US20130184141A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US15/016,195 US10597333B2 (en) 2012-01-18 2016-02-04 Process for producing ceramic fiber-reinforced composite material

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2012007738A JP5916088B2 (ja) 2012-01-18 2012-01-18 セラミック繊維強化複合材料の製造方法およびセラミック繊維強化複合材料
JP2012-007738 2012-01-18

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US15/016,195 Division US10597333B2 (en) 2012-01-18 2016-02-04 Process for producing ceramic fiber-reinforced composite material

Publications (1)

Publication Number Publication Date
US20130184141A1 true US20130184141A1 (en) 2013-07-18

Family

ID=47563268

Family Applications (2)

Application Number Title Priority Date Filing Date
US13/743,293 Abandoned US20130184141A1 (en) 2012-01-18 2013-01-16 Process for producing ceramic fiber-reinforced composite material and ceramic fiber-reinforced composite material
US15/016,195 Active 2034-10-26 US10597333B2 (en) 2012-01-18 2016-02-04 Process for producing ceramic fiber-reinforced composite material

Family Applications After (1)

Application Number Title Priority Date Filing Date
US15/016,195 Active 2034-10-26 US10597333B2 (en) 2012-01-18 2016-02-04 Process for producing ceramic fiber-reinforced composite material

Country Status (3)

Country Link
US (2) US20130184141A1 (ja)
EP (1) EP2617694B1 (ja)
JP (1) JP5916088B2 (ja)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160083300A1 (en) * 2014-09-18 2016-03-24 Toto Ltd. Process for producing reaction bonded silicon carbide member
US20170166486A1 (en) * 2015-12-11 2017-06-15 University Of The Witwatersrand, Johannesburg Ceramic composite and method to prepare the composite
CN109415275A (zh) * 2016-09-06 2019-03-01 株式会社Ihi 陶瓷基复合材料的制造方法
EP3505502A4 (en) * 2016-08-25 2020-03-25 IHI Corporation CERAMIC-BASED COMPOSITE MATERIAL AND METHOD FOR THE PRODUCTION THEREOF
US20220388912A1 (en) * 2021-06-04 2022-12-08 Raytheon Technologies Corporation Through thickness reinforcement

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9701591B2 (en) 2011-10-12 2017-07-11 United Technologies Corporation Method for fabricating a ceramic material
US9701578B2 (en) * 2013-03-15 2017-07-11 Rolls-Royce Corporation Reactive melt infiltrated-ceramic matrix composite
US9650303B2 (en) * 2013-03-15 2017-05-16 Rolls-Royce Corporation Silicon carbide ceramic matrix composites
WO2014168921A1 (en) * 2013-04-09 2014-10-16 United Technologies Corporation Method for fabricating a ceramic material
JP2017119589A (ja) * 2015-12-28 2017-07-06 イビデン株式会社 セラミック複合材及びセラミック複合材の製造方法
JP6981778B2 (ja) * 2017-05-29 2021-12-17 イビデン株式会社 ＳｉＣ繊維強化セラミック複合材の製造方法
CN110670002A (zh) * 2019-10-30 2020-01-10 湖南易兴建筑有限公司 陶瓷合金材料及其制备方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0519641A1 (en) * 1991-06-17 1992-12-23 General Electric Company Silicon carbide composite with coated fiber reinforcement and method of forming

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3673011B2 (ja) * 1996-03-29 2005-07-20 株式会社東芝 セラミックス基繊維複合材料およびその製造方法
US5955391A (en) * 1996-03-29 1999-09-21 Kabushiki Kaisha Toshiba Ceramic matrix composite and method of manufacturing the same
JPH1059780A (ja) 1996-08-20 1998-03-03 Toshiba Corp セラミックス基繊維複合材料およびその製造方法
JPH10167831A (ja) 1996-12-16 1998-06-23 Ngk Insulators Ltd ＳｉＣ繊維強化Ｓｉ−ＳｉＣ複合材料及びその製造方法
JP2952206B2 (ja) 1997-03-19 1999-09-20 川崎重工業株式会社 ガラス含浸繊維強化セラミックスおよびその製造方法
DE19711829C1 (de) * 1997-03-21 1998-09-03 Daimler Benz Ag Verfahren zur Herstellung einer faserverstärkten Verbundkeramik
US5952100A (en) * 1997-05-21 1999-09-14 General Electric Company Silicon-doped boron nitride coated fibers in silicon melt infiltrated composites
JPH11263668A (ja) 1998-03-18 1999-09-28 Toshiba Corp セラミックス基繊維複合材料部品とその製造方法
RU2160790C2 (ru) * 1998-07-07 2000-12-20 Институт физики твердого тела РАН Композиционный жаропрочный и жаростойкий материал
JP3096716B1 (ja) * 1999-03-01 2000-10-10 工業技術院長 繊維強化炭化ケイ素複合材の製造方法
US6609452B1 (en) * 2000-01-11 2003-08-26 M Cubed Technologies, Inc. Silicon carbide armor bodies, and methods for making same
US6764620B1 (en) * 2001-11-28 2004-07-20 The United States Of America As Represented By The United States Department Of Energy Reaction-forming method for producing near net-shape refractory metal carbides
US7297368B2 (en) * 2003-04-15 2007-11-20 Ultramet Method of making carbon fiber-carbon matrix reinforced ceramic composites
FR2869609B1 (fr) * 2004-05-03 2006-07-28 Snecma Propulsion Solide Sa Procede de fabrication d'une piece en materiau composite thermostructural
US9120705B2 (en) * 2006-06-16 2015-09-01 United Technologies Corporation Refractoryceramic composites and methods of making
US20120177488A1 (en) * 2009-03-27 2012-07-12 General Electric Company Process for joining silicon-containing ceramic articles and components produced thereby

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0519641A1 (en) * 1991-06-17 1992-12-23 General Electric Company Silicon carbide composite with coated fiber reinforcement and method of forming

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160083300A1 (en) * 2014-09-18 2016-03-24 Toto Ltd. Process for producing reaction bonded silicon carbide member
US9994487B2 (en) * 2014-09-18 2018-06-12 Toto Ltd. Process for producing reaction bonded silicon carbide member
US20170166486A1 (en) * 2015-12-11 2017-06-15 University Of The Witwatersrand, Johannesburg Ceramic composite and method to prepare the composite
US10040724B2 (en) * 2015-12-11 2018-08-07 University Of The Witwatersrand, Johannesburg Ceramic composite and method to prepare the composite
EP3505502A4 (en) * 2016-08-25 2020-03-25 IHI Corporation CERAMIC-BASED COMPOSITE MATERIAL AND METHOD FOR THE PRODUCTION THEREOF
US11548828B2 (en) 2016-08-25 2023-01-10 Ihi Corporation Ceramic matrix composite and method of manufacturing the same
CN109415275A (zh) * 2016-09-06 2019-03-01 株式会社Ihi 陶瓷基复合材料的制造方法
US20200024199A1 (en) * 2016-09-06 2020-01-23 Ihi Corporation Production method of ceramic matrix composite
US10961161B2 (en) * 2016-09-06 2021-03-30 Ihi Corporation Production method of ceramic matrix composite
CN109415275B (zh) * 2016-09-06 2021-08-24 株式会社Ihi 陶瓷基复合材料的制造方法
US20220388912A1 (en) * 2021-06-04 2022-12-08 Raytheon Technologies Corporation Through thickness reinforcement

Also Published As

Publication number Publication date
JP5916088B2 (ja) 2016-05-11
US10597333B2 (en) 2020-03-24
EP2617694A1 (en) 2013-07-24
EP2617694B1 (en) 2018-06-13
US20160145158A1 (en) 2016-05-26
JP2013147366A (ja) 2013-08-01

Similar Documents

Publication Publication Date Title
US10597333B2 (en) Process for producing ceramic fiber-reinforced composite material
US4944904A (en) Method of obtaining a fiber-containing composite
US5015540A (en) Fiber-containing composite
JP6170160B2 (ja) Ｃｍｃ製部品の製造方法
JP6411894B2 (ja) セラミックマトリックス複合材を製造する方法およびそれによって形成されたセラミックマトリックス複合材
US5021367A (en) Fiber-containing composite
US20210292245A1 (en) Method for manufacturing a part made from cmc
RU2668431C2 (ru) Способ получения деталей из композитного материала путем пропитки композицией с низкой температурой плавления
US7628942B1 (en) Resin infiltration transfer technique
EP2578555B1 (en) Method of fabricating a ceramic component
US11548828B2 (en) Ceramic matrix composite and method of manufacturing the same
EP2578556B1 (en) Method and ceramic component
Radhika et al. A review on Si-based ceramic matrix composites and their infiltration based techniques
EP3252025B1 (en) Method for ceramic matrix composite with carbon coating for wetting
CN111801305A (zh) 用于制造cmc组件的方法
Weiß Carbon/carbons and their industrial applications
Rocha et al. Formation of carbon fiber-reinforced ceramic matrix composites with polysiloxane/silicon derived matrix
US20190023618A1 (en) Composite material and method for making
EP3568382B1 (en) Melt infiltration with siga and/or siin alloys
KR102203084B1 (ko) 복합 프리폼 및 이를 포함하는 탄소 복합체
GB2250516A (en) Fiber-containing composite
JP4616442B2 (ja) 耐酸化保護層を有する炭素質材料およびその製造方法
Liu et al. Research on manufacturing process of carbon-carbon composites as ablation resistance materials
JP2002137978A (ja) 耐酸化保護層を有する炭素質材料の製造方法

Legal Events

Date Code Title Description
AS Assignment

Owner name: JAPAN AEROSPACE EXPLORATION AGENCY, JAPAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:OGASAWARA, TOSHIO;AOKI, TAKUYA;KOTANI, MASAKI;REEL/FRAME:029644/0497

Effective date: 20121228

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION