US20020019071A1 - Composite material impregnated with metal silicide and process for producing the same - Google Patents

Composite material impregnated with metal silicide and process for producing the same Download PDF

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Publication number
US20020019071A1
US20020019071A1 US09/854,757 US85475701A US2002019071A1 US 20020019071 A1 US20020019071 A1 US 20020019071A1 US 85475701 A US85475701 A US 85475701A US 2002019071 A1 US2002019071 A1 US 2002019071A1
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Prior art keywords
silicide
composite
metal silicide
composite material
yarn
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US09/854,757
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Shigeru Hanzawa
Naoki Hashimoto
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NGK Insulators Ltd
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NGK Insulators Ltd
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Assigned to NGK INSULATORS, LTD. reassignment NGK INSULATORS, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HANZAWA, SHIGERU, HASHIMOTO, NAOKI
Publication of US20020019071A1 publication Critical patent/US20020019071A1/en
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    • 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
    • C04B41/5053—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 non-oxide ceramics
    • C04B41/5062—Borides, Nitrides or Silicides
    • C04B41/5071—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
    • 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
    • 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
    • C04B2103/00—Function or property of ingredients for mortars, concrete or artificial stone
    • C04B2103/0004—Compounds chosen for the nature of their cations
    • C04B2103/0017—Refractory metal compounds
    • 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
    • C04B2111/00—Mortars, concrete or artificial stone or mixtures to prepare them, characterised by specific function, property or use
    • C04B2111/00474—Uses not provided for elsewhere in C04B2111/00
    • C04B2111/00982—Uses not provided for elsewhere in C04B2111/00 as construction elements for space vehicles or aeroplanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/29—Coated or structually defined flake, particle, cell, strand, strand portion, rod, filament, macroscopic fiber or mass thereof
    • Y10T428/2913—Rod, strand, filament or fiber
    • Y10T428/2933—Coated or with bond, impregnation or core
    • Y10T428/2971—Impregnation

Definitions

  • the present invention relates to composite materials impregnated with a metal silicide, which have a surface layer having a superior oxidation resistance at elevated temperatures and also superior properties in mechanical strength, and processes for producing the same.
  • An object of the present invention is to provide a composite material, which retains mechanical strength at a given level and, at the same time, possesses a good balance in terms of lightweight properties and resistance to oxidation, abrasion, and heat, and a process for producing the same.
  • the inventors have carried out extensive investigations in light of the present state as described above, and in consequence obtained the finding that the above-described object is achieved by a composite material that can be produced especially by impregnating a particular metal silicide into a C/C composite or a carbonaceous composite material utilizing the C/C composite as a starting material, leading to the present invention.
  • a composite material impregnated with a metal silicide characterized by comprising a metal silicide and a C/C composite impregnated with at least the metal silicide; a composite material characterized in that the metal silicide has a melting point of at least 1400° C.
  • the composite material characterized in that the metal silicide is at least one selected from the group consisting of titanium silicide, zirconium silicide, tantalum silicide, niobium silicide, chromium silicide, tungsten silicide, and molybdenum silicide; the composite material characterized in that the C/C composite is tubular, cylindrical, perforated-disc-shaped, or angular; and the composite material characterized in that the C/C composite is composed of carbon and carbon fiber and has a porosity of 5% to 50% before impregnating the metal silicide.
  • a process for producing a composite material comprising a metal silicide and a C/C composite impregnated with at least the metal silicide, characterized by holding a basal material and a metal silicide in an inert atmosphere at a temperature in the vicinity of the melting point of the metal silicide for a desired period of time to impregnate the C/C composite with the metal silicide, wherein the basal material is selected from C/C composites and carbonaceous composite materials utilizing C/C composites as a starting material; the process for producing a composite material, characterized in that the metal silicide has a melting point of at least 1400° C.
  • the process for producing a composite material characterized in that the metal silicide is at least one selected from the group consisting of titanium silicide, zirconium silicide, tantalum silicide, niobium silicide, chromium silicide, tungsten silicide, and molybdenum silicide; and the process for producing a composite material, characterized in that the metal silicide is impregnated at an amount in the range of 1% to 50% by weight.
  • FIG. 1 is a schematic perspective view showing a structure of a yarn assembly constituting a basic structure of a C/C composite for use in producing composite materials of the present invention.
  • FIG. 2( a ) is a sectionalviewof aSi-SiC-basedcomposite material taken along line II a -II a of FIG. 1.
  • FIG. 2( b ) is a sectional view of the same material taken along line II b -II b of FIG. 1.
  • FIG. 3 ( a ) is a sectional view of a SiC-based composite material taken along line II a -II a of FIG. 1.
  • FIG. 3( b ) is a sectional view of the same material taken along line II b -II b of FIG. 1.
  • FIG. 4 is EDS photographs showing the sectional str ucture of a composite material impregnated with tungsten disilicide, according to the present invention, indicating a state of impregnation of (a) metallic silicon and (b) metallic tungsten.
  • a composite material impregnated with a metal silicide characterized by comprising a metal silicide and a C/C composite impregnated with at least the metal silicide, as a basal material, a C/C composite composed mainly of amorphous carbon and carbon fibers or a carbonaceous composite material utilizing a C/C composite as a staring material, i.e., a Si-SiC- or Si-based composite material that is a composite material having as a basal material a C/C composite in which layers made up of silicon silicide are formed by impregnating the C/C composite with metallic silicon to react at least a portion of the metallic silicide with carbon are suitably used.
  • a C/C composite is a shaped article or a burned article obtained by burning the shaped article which is obtained by preparing carbon fiber bundles by including pitch, coke, or the like capable of forming free carbon on the carbon fiber bundles after burning and that is a powder binder serving as matrix for the carbon fiber bundles, and optionally incorporating phenolic resin powder or the like, forming a flexible coating of plastics such as thermoplastic resins around these carbon fiber bundles to produce preformed yarns as a flexible intermediate, forming these preformed yarns into sheet-shaped or woven-cloth-like articles by means of the method described in Japanese Patent Application Laid-open No. 2-80639, and laminating them at a desired amount, followed by hot pressing.
  • C/C composite which can be produced by methods repeating infiltration of tar or pitch into carbon fibers and burning or by methods allowing processes such as CVI and CVD to afford carbon to carbon fibers.
  • Carbon fibers are, for example, long, short, and chopped fibers, and are not specified to a particular type or brand.
  • a C/C composite in the context of the present invention is referred to a composite material composed of carbon fibers and carbon other than carbon fiber and having a structure in which the carbon fibers constitute a laminated structure consisting of a particular number of carbon fiber bundles and the carbon other than carbon fiber forms a matrix to fill voids between the laminated structures, i.e., characterized by having a structure of a particular laminated structure and a matrix.
  • the C/C composites are not limited to a particular configuration, as long as carbon fibers and carbon are the major component materials.
  • a C/C composite impregnated with at least a metal silicide means any material in which a C/C composite, a basal material, is impregnated with a metal silicide, and a resulting product produced by impregnating any material in which a Si-SiC- or Si-based composite material described in detail below with a metal silicide. That is, the expression “impregnated with at least metal silicide” means a state where metallic silicon and silicon carbide (Si-SiC) or silicon carbide (SiC) is impregnated in addition to the one where a desired amount of metal silicide is impregnated.
  • articles can be used which are obtained by gathering, in general, hundreds to dozens of thousands of carbon fibers having a diameter of about 10 ⁇ m to form fiber bundles (yarns), obtaining flexible filamentous intermediates prepared by coating the yarns with a thermoplastic resin, forming them into sheet-shaped articles by the method described in Japanese Patent Application Laid-open No.
  • the carbon component other than carbon fiber in the above-mentioned yarns is preferably carbon powder, and particularly preferably graphitized carbon powder.
  • a Si-SiC-based composite material which is one type of the carbonaceous composite materials utilizing as a starting material a C/C composite used as a basal material in the present invention or which is one type of composite material in which a C/C composite is impregnated with metallic silicon and at least a portion of the metallic silicon is reacted with carbon to form layers of silicon carbide, is referred to a composite material composed of 55% to 75% by weight of carbon, 1% to 10% by weight of silicon, and 10% to 50% by weight of silicon carbide, provided with a yarn assembly integrated in such a way that yarns containing at least bundles of carbon fibers and a carbon component other than carbon fiber are ordered in the yarn direction and additionally combined three-dimensionally to prevent from detaching them to each other and a matrix of Si-SiC-based material with which voids between the neighboring yarns within the yarn assembly are filled, and having a coefficient of kinetic friction of 0.05 to 0.6 and a controlled porosity of 0.5% to 10%.
  • a Si-SiC-based material typically comprises a silicon phase and silicon carbide phases, including several different phases varying from a silicon phase of silicon remaining at an unreacted state to a phase of almost pure silicon carbide, and the silicon carbide phases can include SiC co-existing phases having a gradient change in the content of silicon. Therefore, a Si-SiC-based material is collectively referred to materials containing a carbon concentration within the range of 0 to 50 mol% in the Si-SiC series. For a Si-SiC-based composite material relating to the present invention, it is understood that the matrix region is formed of the Si-SiC-based material.
  • these Si-SiC-based composite materials preferably have a matrix with a gradient composition with the percent content of silicon increasing as the distance from the yarn surface is increased.
  • the yarn assembly made up of carbon fibers is composed of a plurality of yarn alignments.
  • Each yarn alignment is formed by arranging yarns almost in parallel and two-dimensionally, the yarns made up by gathering a particular number of carbon fibers, and the yarn alignments are laminated to make up the yarn assembly. This allows Si-SiC-based composite materials to possess a laminated structure in which a plurality of layers of the yarn alignments are laminated in a specific direction.
  • FIG. 2( a ) is a sectional view taken along line II a -II a of FIG. 1.
  • FIG. 2( b ) is a sectional view taken along line II b -II b of FIG. 1.
  • Yarn assembly 6 constitutes the backbone of Si-SiC-based composite material 7 .
  • Yarn assembly 6 comprises laminating yarn alignments 1 A, 1 B, 1 C, 1 D, 1 E, 1 F in the vertical direction.
  • each yarn 3 is arranged two-dimensionally, and is almost parallel in its longitudinal direction.
  • Each yarn alignment neighboring in the vertical direction crosses at right angles in the longitudinal direction of each yarn.
  • each yarn 2 A in each of yarn alignments 1 A, 1 C, 1 E is parallel to each other in the longitudinal direction, and crosses at right angles to each yarn 2 B in each of yarn alignments 1 B, 1 D, 1 F in the longitudinal direction of yarn 2 B.
  • Each yarn is made up by fiber bundles 3 composed of carbon fibers and a carbon component other than carbon fiber.
  • the laminating of the yarn alignments results in constituting the yarn assembly 6 in the form of a three-dimensional grid.
  • Each yarn is pressed during the molding step under pressure and formed to an oval-like figure.
  • each of yarn alignments 1 A, 1 C, 1 E the spaces between the neighboring yarns are filled with matrix 8 A, each matrix 8 A extending parallel to yarn 2 A along its surface.
  • the spaces between the neighboring yarns are filled with matrix 8 B, each matrix 8 B extending parallel to yarn 2 B along its surface.
  • matrices 8 A and 8 B are composed of silicon carbide phases 4 A and 4 B coating the surface of each yarn, and Si-SiC-based material phases 5 A and 5 B having a smaller content of carbon than that of silicon carbide phases 4 A and 4 B, respectively. Silicon can be contained also in the silicon carbide phases to a small degree. Furthermore, in this example, there are formed silicon carbide phases 4 A and 4 B between vertically neighboring yarns 2 A and 2 B as well. Each of matrices 8 A and 8 B extends narrowly and longitudinally along the surface of each yarn, preferably linearly, and crosses mutually at right angles.
  • Matrix 8 A within yarn alignments 1 A, 1 C, 1 E and matrix 8 B within yarn alignments 1 B, 1 D, 1 F crossing at right angles to them are connected at the voids between yarns 2 A and 2 B, respectively. Consequently, matrices 8 A and 8 B form a three-dimensional grid as a whole.
  • a SiC-based composite material that is a second material of the carbonaceous composite materials utilizing as starting material a C/C composite used as a basal material in the present invention and that is a composite material in which layers made up of silicon carbide are formed by impregnating a C/C composite with metallic silicon to react at least a portion of the metallic silicon with carbon is referred to a composite material of Si-SiC composites composed of silicon carbide, carbon fibers, and a carbon components other than carbon fiber and having a structure comprising the backbone region and matrix formed around the backbone region, wherein at least 50% of the silicon carbide is ⁇ -type, wherein the backbone region is formed of the carbon fibers and carbon component other than carbon fiber and the silicon carbide can be present in a portion of the backbone region, wherein the matrix is formed of the silicon carbide, and the matrix and the backbone region are formed integrally, and wherein the composite material has a porosity of 0.5% to 5% and a two-peaked distribution of the average
  • these SiC-base composite materials utilize as the backbone region a C/C composite in which each of carbon fibers is composed of carbon fiber bundles, and thus have a significant feature of almost retaining mechanical strength which the raw material C/C composite possesses or increasing it by the formation of silicon carbide, since even if SiC is formed on their portion, each of carbon fibers retains the structure as carbon fiber without breaking so that carbon fibers do not break into shorter fibers due to formation of silicon carbide.
  • a matrix made up of SiC-based material is formed between the neighboring yarns in the yarn assembly. In this point, these materials are different from the above-mentioned Si-SiC-based composite materials.
  • These materials can be produced by the method disclosed in Japanese Patent Application No. 11-31979, filed on Feb. 9, 1999, the content of which is incorporated herein by reference. These materials also have a coefficient of kinetic friction in the range of 0.05 to 0.6.
  • a SiC-based material is referred to material containing silicon carbides having different degrees of binding with carbon.
  • Such a SiC-based material can be produced as described below.
  • a C/C composite is impregnated with metallic silicon.
  • the metallic silicon reacts with carbon atoms making up the carbon fibers within the composite and/or free carbon atoms remaining on the surface of the carbon fibers and its portion undergoes carbonization, so that partially carbonized silicon is formed on the outermost surface of the C/C composite and between the yarns made up of the carbon fibers, and thus resulting in the formation of matrix made up of silicon carbide between the above-mentioned yarns.
  • the matrix can contain several, different phases ranging from a silicon-carbide-like phase resulting from combining an extremely small amount of silicon and carbon to a crystal phase of pure silicon carbide.
  • the matrix contains only metallic silicon not more than a detection limit by X-ray (0.3% by weight). That is, the matrix typically comprises the silicon carbide phase, and the silicon carbide phase can contain SiC-like phases having a gradual change in the content of silicon. Therefore, a SiC-based material is collectively referred to materials containing a carbon concentration within the range of not less than at least 0.01 to 50 mol% in the SiC series.
  • FIG. 3( a ) shows a sectional view of a SiC-based composite material relating to the present invention when taken along line II a -II a of FIG. 1
  • FIG. 3( b ) shows a sectional view of the same when taken along line II b -II b of FIG. 1.
  • the backbone of SiC-based composite material 17 is composed of yarn assembly 16 , similarly to that of Si-SiC-based composite material 7 .
  • Yarn assembly 16 comprises laminating yarn alignments 11 A, 11 B, 11 C, 11 D, 11 E, 11 F in the vertical direction.
  • each yarn 13 is arranged two-dimensionally, and is almost parallel in the longitudinal direction.
  • Each yarn in each of the vertically neighboring alignments crosses at right angles in the longitudinal direction. That is, each yarn 12 A in each of yarn alignments 11 A, 11 C, 11 E is parallel to each other in the longitudinal direction, and crosses at right angle to each yarn 12 B in each of yarn alignments l 1 B, 11 D, 11 F in the longitudinal direction of yarn 12 B.
  • Each yarn is composed of fiber bundles 13 consisting of carbon fibers and a carbon component other than carbon fiber. The laminating of the yarn alignments results in constituting the yarn assembly 16 in the form of a three-dimensional grid. Each yarn is pressed during the molding step under pressure and formed to an oval-like figure.
  • each of yarn alignments 11 A, 11 C, 11 E the spaces between the neighboring yarns are filled with matrix 18 A, each matrix 18 A extending parallel to yarn 12 A along its surface.
  • the spaces between the neighboring yarns are filled with matrix 18 B, each matrix 18 B extending parallel to yarn 12 B along its surface.
  • each of matrices 18 A and 18 B is composed of silicon carbide phase 14 coating the surface of each yarn. A portion of the silicon carbide phase may protrude from the surface as small protrusion 19 , or into a carbon fiber layer in the inside of the composite components.
  • pores 15 there are formed pores (voids 15 ) having a median of the pore size of about 100 ⁇ m. Since these small protrusions 19 are formed along sites of matrices mainly made up of a carbon component or components other than the carbon fibers of the raw-material C/C composite, it is possible to adjust the density of small protrusion 19 in a unit area by selecting the distance between yarns and/or between yarn alignments, as appropriate. Silicon carbide phase 14 can be formed also between neighboring yarns 12 A and 12 B.
  • Each of matrices 18 A and 18 B extends narrowly and longitudinally along the surface of each yarn, preferably linearly, and crosses mutually at right angles. Matrix 18 A within yarn alignments 11 A, 11 C, 11 E and matrix 18 B within yarn alignments 11 B, 11 D, 11 F crossing at right angles to them are connected at the spaces between yarns 12 A and 12 B, respectively. Consequently, matrices 18 A and 18 B form a three-dimensional grid as a whole.
  • metal silicides to be used as material for impregnation are used ones having a melting point of at least 1400° C. or higher.
  • such metal silicides include titanium silicide, zirconium silicide, tantalum silicide, niobium silicide, chromium silicide, tungsten silicide, molybdenum silicide, and others.
  • the reason of using metal silicides having a melting point of at least 1400° C. or higher is that they are necessary for retaining a desired resistance to oxidation at 1000° C.
  • the manufacturing can be carried out by keeping both materials described above in an inert atmosphere for a desired period at a temperature in the vicinity of the melting point of the metal silicide to melt the metal silicide and impregnating the melted metal silicide into the above-mentioned composite material produced by impregnating a C/C composite or the like with metallic silicon.
  • both materials can be placed into a single container and heated to a pre-determined temperature to melt the metal silicide, followed by applying pressure within the container or maintaining the inside of the container under reduced pressure to impregnate the melted metal silicide into a C/C composite or the like.
  • Conditions during impregnation such as the temperature for melting, pressure to be applied or degree of reduced pressure, and holding period, can be set as appropriate, taking properties of the metal silicide to be used and others into account.
  • the amount of impregnation can be varied, depending on various properties, such as the porosity of a C/C composite as the basal material, the fluidity of the melted metal silicide, and is usually 1 to 50%, as expressed in % by weight. At less than 1% by weight, effects of improving mechanical strength by metal silicide impregnation are not observed, and also resistance to oxidation is not increased. Impregnation at more than 50% may cause problems, for example, of increasing the manufacturing cost due to various limitations on manufacturing, and, at the same time, increase in the specific weight of composite materials, relative to that of C/C composites, with not being preferable. Accordingly, composite materials excellent in mechanical strength with a bending strength of 150 MPa or higher and a coefficient of kinetic friction of 0.5 ⁇ or less can be obtained.
  • Carbon fibers were put and set unidirectionally, and then impregnated with a phenolic resin. About ten thousands of long carbon fibers with a diameter of 10 ⁇ m were gathered to produce a fiber bundle (yarn). Yarn alignments (prepreg sheets) into which these yarns were formed were made and arranged as shown in FIG. 3 to produce a prepreg sheet laminate, to which a carbon-based adhesive was applied to fasten the yarns mutually. The prepreg sheet laminate thus obtained was wound around a cylindrical carbon fiber having a diameter of 15 mm, onto which a carbon-based adhesive was applied to fasten the yarns mutually. After fastening, the cylindrical prepreg sheet laminates were put into an oven to cure the impregnated phenolic resin at 180° C. and at normal pressure, followed by burning them at 2000° C. under a nitrogen atmosphere to obtain C/C composites.
  • a series of C/C composites obtained in ( 1 ) as described above and having an outer diameter of 30mm and an entire length of 200 cm was used as a basal material.
  • a given amount of titanium silicide, zirconium silicide, tantalum silicide, niobium silicide, chromium silicide, tungsten silicide, or molybdenum silicide was kept at a pre-determined temperature to melt. Then each of thus melted silicides was separately impregnated into the individual above-mentioned basal material.
  • the bending strength was measured according to JIS R 1601 .
  • the coefficient of kinetic friction is a coefficient of friction between the same materials at a stabilized condition after sliding them at a dry state under a pressing pressure of 40 kg/cm 2 and at a rotating speed of 200 rpm for a few minutes.
  • FIG. 4( a ) and 4 ( b ) Examples of the sectional structure that is a feature of composite materials relating to the present invention are shown in FIG. 4( a ) and 4 ( b ) as an EDS photograph of the sectional structure of the composite material obtained by impregnation of tungsten disilicide. White regions in the figures indicate high concentrations of the examined element. It can be found from FIGS. 4 ( a ) and 4 ( b ) that both silicon and tungsten are almost uniformly impregnated into the C/C composite precursor.
  • composite materials that can be produced by the methods according to the present invention are, of course, superior in resistance to oxidation, and are a new material having a good balance also in terms of mechanical strength and lightweight properties, and useful as constituent material of various components for aerospace applications and others requiring resistance to heat, corrosion, abrasion, and oxidation.

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WO2007087481A2 (en) * 2006-01-26 2007-08-02 Ucar Carbon Company Inc. Anti-oxidation coating for carbon composites

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FR2925044B1 (fr) * 2007-12-13 2010-03-12 Snecma Propulsion Solide Procede de realisation d'une couche de carbure refractaire sur une piece en materiau composite c/c.
WO2017192674A1 (en) * 2016-05-03 2017-11-09 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Refractory metal silicide nanoparticle ceramics

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RU2082824C1 (ru) * 1994-03-10 1997-06-27 Московский государственный авиационный институт (технический университет) Способ защиты жаропрочных материалов от воздействия агрессивных сред высокоскоростных газовых потоков (варианты)
US6107225A (en) * 1997-10-23 2000-08-22 Agency Of Industrial Science And Technology High-temperature ceramics-based composite material and its manufacturing process
JP3543105B2 (ja) * 1998-02-26 2004-07-14 独立行政法人産業技術総合研究所 易加工性高温用複合材料およびその製造方法

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* Cited by examiner, † Cited by third party
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WO2007087481A2 (en) * 2006-01-26 2007-08-02 Ucar Carbon Company Inc. Anti-oxidation coating for carbon composites
WO2007087481A3 (en) * 2006-01-26 2008-01-24 Ucar Carbon Co Inc Anti-oxidation coating for carbon composites

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EP1157979A2 (de) 2001-11-28
EP1157979B1 (de) 2004-12-15
DE60107755T2 (de) 2005-12-08
EP1157979A3 (de) 2002-07-24
JP2001328887A (ja) 2001-11-27
DE60107755D1 (de) 2005-01-20

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