Abstract: A fiber reinforced composite article, comprising a matrix and reinforcing fibers and subjected during operation concurrently to a plurality of temperatures and stresses, varying between a plurality of regions of the article, experiences different stresses concurrently in different regions of the article. The article is provided with fiber reinforcement of a strength in each region greater than the stress experienced in that region. Such fiber reinforcement is provided through a member for inclusion in the matrix, for example in the form of at least one of a fabric, weave, braid, lay-up, etc. One form of such an article for use at relatively high temperatures is a turbine engine component, for example a gas turbine engine exhaust flap. Another form of such an article is a gas turbine engine blading component.

Abstract: A reinforced vitreous carbon composite suitable for use in the formation of wear-resistant assemblies, such as joint prosthetic devices, bearings, current collectors, sealing components, brake linings, electrical motor brushes, and other tribological products. The reinforced composite is formed by impregnating a metal reinforcement structure with a furfuryl alcohol resin, and polymerizing the resin while thermally managing the polymerization process, to produce a poly(furfuryl) alcohol continuous phase that is isotropic, homogeneous and essentially completely void-free, e.g., in a bulk composite form having dimensions greater than 25 millimeters in each of the x, y and z directions thereof.

Abstract: Non-oxide debond coated reinforcing fibers that are resistant to oxidation at temperatures above about 1200° C. are described. The debond coatings are non-hygroscopic, and exhibit debond performance equal to or better than the prior art such coatings. The coated fibers of the present invention comprise a non-oxide fiber with or without a thin conventionally applied pyrolytic carbon layer overcoated with a non-hygroscopic silicon and titanium containing single or multi-layer structure that imparts all of the properties demanded of a debond coating while additionally providing exceptional oxidation resistance protection.

Abstract: A process for manufacturing an inorganic material-based article comprising the steps of

Abstract: A friction liner for a dry friction clutch for a motor vehicle comprises a friction material made by a method which includes the impregnation of a mineral fiber based yarn with an aqueous impregnating cement, which contains latex and a phenolic resin which is at least partly in the form of a phenolate.

Abstract: A friction or sliding body includes at least two composite materials reinforced with fiber bundles and containing a ceramics matrix. A first composite material forms the outside of the sliding body as a friction layer and a second composite material forms a supporting body joined areally to the friction layer. The fiber bundle lengths of the friction layer are significantly shorter than the fiber bundle lengths of the supporting body. The fiber bundles of the friction layer have a clear alignment perpendicular to the surface. The surface of the friction layer is formed substantially only of small regions of free carbon with a diameter of at most 1.2 mm, and a total fraction of the area of free carbon on the surface is at most 35%. The surface has an extremely fine crack structure and the friction layer exhibits virtually no stresses in the vicinity of the surface. A process for producing a friction or sliding body and a brake disc or brake lining are also provided.

Abstract: Disclosed are an oxide matrix composite that is stable for long-term exposures to temperatures of approximately 1,200° C. and the methods of making the ceramic matrix composite, including wet lay-up, prepreg, and filament winding fabrication methods. The oxide matrix composite can be made using commercially available refractory fibers that retain better than 85% of its original composite strength after 1,000 hours of exposure to such high temperature environments. The preferred alumina-based system demonstrates damage tolerance as relatively high strength retention properties and structural performance. The preferred refractory fibers are commercially available under the tradename of NEXTEL® 720.

Abstract: A shaped thermal insulation body comprises molded and/or sintered thermal insulation material and contains fumed silica, inorganic fillers, opacifiers and fibers. The BET surface of the thermal insulation material is below 100 m2/g, e.g. between 10 and 100 m2/g, so that the shaped thermal insulation body absorbs less water. In the case of radiant heaters, the shaped thermal insulation body can be used as a base for heating resistors.

Abstract: A protective structure for thermal insulation and impact resistance, and especially suited for bonded application to the exterior of aircraft including spacecraft to protect the craft from high temperatures generated by exhaust gases and by atmospheric re-entry. The structure includes either a single ceramic tile component with a cover component comprising a fiber reinforced ceramic matrix composite encasing the tile component, or a plurality of ceramic tile components with a like single cover component encasing the plurality of tile components. Utilizing the structures as an external aircraft surface imparts a super hard exterior that functions to significantly prohibit impact and erosion damage while not compromising the desirable thermal insulation properties inherent to tile.

Abstract: Polyurethane elastomer yams (particularly spandex) containing certain silver-based antimicrobial formulations therein are provided. This invention relates to polyurethane elastomer yams (particularly spandex) containing certain silver-based antimicrobial formulations therein. Such formulations comprise antimicrobial compounds, such as, preferably, triclosan and/or silver-containing ion-exchange resins, such as zirconium phosphate, glass, and/or zeolite compounds. The inventive spandex yarns exhibit excellent antimicrobial qualities as well as surprisingly good anti-tack/frictional characteristics. As a result, antimicrobial spandex yams are provided which exhibit ease in processing, particularly in further knitting, weaving, etc., to produce fabrics therefrom. Such fabrics are also encompassed within this invention.

Abstract: In a friction material including a fibrous reinforcement, a friction modifier and a binder, no whisker-like potassium titanate fiber is contained, but powdery or flaky potassium titanate with an aspect ratio of not higher than 3 is mixed as a friction component. The diameter of the powdery or flaky potassium titanate is preferably in a range of from 0.05 &mgr;m to 150 &mgr;m. In addition, the powdery or flaky potassium titanate is preferably subjected to surface treatment with a silane coupling agent, phenolic resin, or the like. Further, fibrous potassium titanate may be mixed at a volume ratio of not higher than 30% with respect to the powdery or flaky potassium titanate. The fibrous potassium titanate is a by-product when the powdery or flaky potassium titanate is produced and which has a length of not longer than 5 &mgr;m or a diameter of not smaller than 3 &mgr;m.

Abstract: A fiber-composite material includes: 55-75 wt % of carbon, 1-10 wt % of silicon and 10-50 wt % of silicon carbide, and the matrices including Si—SiC-based materials formed integrally among assemblages of yarns include carbon fibers integrally formed and combined three-dimensionally so as not to separate from each other. The fiber-composite material has a coefficient of kinetic friction of 0.05-0.6 and a porosity of 0.5-10%.

Abstract: A method of fabricating a ceramic structure as well as a pre-ceramic preimpregnated composite material incorporating a continuous woven fiber and a discontinuous fiber pre-ceramic matrix for subsequent curing and component construction. The method includes preparation of a mixture of discontinuous fibers, fillers, and a pre-ceramic precursor resin where the precursor resin is present in a quantity sufficient to substantially saturate subsequently adjacent woven fiber lengths, and thereafter introducing the mixture to a situs between an upper length of woven fiber and a lower length of woven fiber in alignment with each other while effectuating linear movement of these woven fiber lengths and moving the lengths toward each other for compression and retention in a sandwich configuration to thereby fabricate a pre-ceramic preimpregnated composite material. The material is cut to size in accord with the configuration of a part to be manufactured, formed into a green-state structure, and cured.

Abstract: A molding material comprises at least the following components A, B and C, with the component C arranged to contact a composite comprising the components A plus B. The components are elongated members identified as: A A continuous reinforcing fiber bundle, B A thermoplastic polymer or oligomer having a weight average molecular weight of 200 to 50,000 and a melt viscosity lower than that of the component C, and C A thermoplastic resin having a weight average molecular weight of 10,000 or more.

Abstract: The present invention is a low density hybrid airfoil comprising a temperature resistant exterior layer and a tough, high impact resistant interior layer. Specifically, the airfoil comprises a monolithic ceramic exterior layer and a fiber reinforced ceramic matrix composite interior layer. Both the monolithic ceramic and fiber reinforced ceramic matrix composite are low density materials. Additionally, the monolithic ceramic is a high temperature resistant material, and the fiber reinforced ceramic matrix composite is a relatively high impact resistant structure. Encapsulating the airfoil with a temperature resistant exterior layer protects the airfoil in a high temperature environment, and supporting the airfoil with a high impact resistant, fiber reinforced ceramic matrix composite improves the overall impact resistance of the airfoil thereby resulting in a tough, high temperature resistant, low density airfoil.

Abstract: A fiber-composite material (7) is comprised of a yarn aggregate (6) in which yam (2A, 2B) including at least a bundle (3) of carbon fiber and a carbon component other than carbon fiber is three-dimensionally combined and integrally formed without separation from each other; and a matrix made of Si—SiC-based materials (4A, 4B, 5A, 5B) filled between the yarn (2A, 2B) adjacent to each other within the yarn aggregate (6).

Abstract: This invention provides a composite material having a matrix of structural material containing embedded zones of soft elastic material and zones of solid relatively high density material within the soft elastic material. By selecting a particular resonance frequency for the subunits of soft elastic material and solid high density material, frequencies just lower than the resonance frequencies will be unable to propagate through the material and be strongly reflected or absorbed. Such material may be used in the manufacture of filters or shields against particular target frequencies. Subunits having a variety of resonance frequencies may provide a broader range of frequencies that the material may shield.

Abstract: A carbon fiber reinforced carbon composite, obtained by a method comprising impregnating a pitch or a resin into a molded member formed of carbon fibers for densification thereof; forming an impregnated pyrolytic carbon layer by CVI after densification; and forming a coated pyrolytic carbon layer on the impregnated pyrolytic carbon layer by CVD; a method of making the carbon fiber reinforced carbon composite; and a pulling single crystal member made from the carbon fiber reinforced carbon composite.

Abstract: A color-developing composite short fiber having a length of 0.01 to 100 mm is obtained by cutting a color-developing short fiber capable of reflecting visible rays and interfering therewith consisting of two or more kinds of polymer compounds having different refractive indices which are laminated alternately, while a color-developing structure is formed by binding particles of the short fiber one another, dispersing the short fiber in or mixing it with other materials to be bound therewith or adhering the short fiber on the surface of a support. Further, a color-developing composite short fiber having a length of 0.

Abstract: Provided are carbon fiber composite materials which have a structure including a skeletal part and a matrix formed integrally around the skeletal part. The skeletal part is mainly composed of carbon fiber bundles and silicon carbide and metallic silicon formed in the carbon fiber bundles and/or on the outer surface of the carbon fiber bundles. The matrix is mainly composed of silicon carbide and metallic silicon. Alternatively, the carbon fiber composite materials have a structure including a skeletal part and a matrix formed integrally around the skeletal part and have a porosity of 0.5-5% and a two-peak type distribution of average pore diameter. The skeletal part is formed of carbon fibers and a carbon component other than the carbon fibers and/or silicon carbide, and the matrix being formed of silicon carbide at least 50% of which is of &bgr; type. These carbon fiber composite materials are suitable for the uses as aerospace materials.

Abstract: A composite doctor blade is provided that is suitable for use in the manufacture of paper, particularly for use in calenders. The composite doctor blade includes multiple layers of composite material in which a substantial proportion of the fibers are aligned in a direction substantially parallel to the long axis of the doctor blade.

Abstract: The invention provides a prepreg, formed by impregnating carbon fiber with an epoxy resin composition comprising an epoxy resin (A) and a curing agent (B) wherein the matrix resin content Wr (wt %) of the prepreg, the 0° tensile modulus E (GPa) of the carbon fiber, and the in-plane shear strength of S (MPa) of the carbon fiber reinforced composition material obtained by heating and curing the prepreg satisfy the following formulae (i) and (ii): S≧205×LOG(E)+610  (i) 15≦Wr≦40  (ii) The prepreg has a high in-plane shear strength, a high mode I interlayer fracture toughness GIC, an excellent CFRP tube in torsion al strength, a high radial compressive strength and a high impact strength and a light weight.

Abstract: A composite material having a preferably rigid preformed ceramic fiber matrix at least partially impregnated with an aerogel and forming a multi-layered material. The matrix is impregnated with an aerogel material which forms a layer having a total thickness r where r is less than t or equal to t, where t is the thickness of the matrix, thus forming a single or multilayered composite material. The material may be formed with numerous layers s1, s2, S3, . . . snn where r=&Sgr;sn and r is less than or equal to t. Thus, a multi-layered material is formed. Alternatively, the aerogel/fiber matrix composite has channels devoid of aerogel.

Abstract: An optically nonisotropic composite material. The composite material includes two materials, a transparent bulk optical material and radiation absorbing or reflecting fibers embedded within the bulk material. The fibers are substantially parallel to one another and tend to channel the radiation along the direction of the fibers. The bulk material may be a scintillator, in which case the fibers will tend to channel scintillating radiation along the direction of the fibers. The composite material may be used in a high spatial resolution x-ray device, such as a CT scanner. The composite material may also be used in an electromagnetic radiation detection device. Advantageously, the fibers tend to channel radiation along the fibers towards photodetector cells of the radiation detection device thereby increasing spatial resolution.

Abstract: The invention provides a method of forming a void-free laminate, comprising the steps of: (a) enclosing a partially impregnated prepreg in a vacuum envelope, said partially impregnated prepreg comprising a fiber layer partially impregnated with a resin composition; and (b) heating said partially impregnated prepreg under vacuum to withdraw air present in said partially impregnated prepreg and to cause said resin composition (i) to fully infuse into said fiber layer and (ii) to cure thereby forming said void-free laminate. The present invention further provides novel combinations of modified epoxy resins that may be employed with the methods disclosed. The void-free laminates may be utilized for the manufacture of parts for the aerospace and aircraft industries.

Abstract: A color-developing composite short fiber having a length of 0.01 to 100 mm is obtained by cutting a color-developing short fiber capable of reflecting visible rays and interfering with visible rays consisting of two or more kinds or polymer compounds having different refractive indices which are laminated alternately. A color-developing structure is formed by binding particles of the short fiber to one another, dispersing the short fiber in a mixture with other materials or adhering the short fiber on the surface of a support. Further, a color-developing composite short fiber having a length of 0.01 to 100 mm is obtained by cutting a color-developing composite fiber comprising two or more polymer compounds having different refractive indices which are laminated alternately forming a layer capable of reflecting visible rays and interfering therewith and a layer capable of reflecting invisible rays and interfering therewith.

Abstract: A debonding layer is formed on fibers such as silicon carbide fibers by forming a thin film of a metal such as nickel or iron on the silicon carbide fibers and then annealing at a temperature of about 350-550° C. to form a debond layer of a metal silicide and carbon. These fibers having the debond coating can be added to composite forming materials and the mixture treated to form a consolidated composite. A one heating-step method to form a consolidated composite involves inserting the silicon carbide fibers with just the initial metal film coating into the composite forming materials and then heating the mixture to form the debond coating in situ on the fibers and to form the consolidated composite. Preferred heating techniques include high temperature annealing, hot-pressing, or hot isostatic pressing (HIP).

Abstract: The heat resisting fiber-reinforced composite material of the invention is a heat-resisting fiber-reinforced composite material used for a product or a part that generates temperature disribution; wherein the thermal expansion coefficient at a portion corresponding to a medium to low temperature range is greater than the thermal expansion coefficient at a portion corresponding to a high temperature range, and the boundary between the portion corresponding to medium to low temperature range and the portion corresponding to the high temperature range is a transition region.

Abstract: Generally, this invention provides a toughened ceramic composite and a method of enhancing the mechanical strength of ceramic matrix composites through use of a transformation weakened interphase material. The ceramic composite provided in this invention includes a ceramic matrix, a second material as a second phase, and a metastable interphase material. The metastable interphase material is positioned between the ceramic matrix and the second phase material. The ceramic composite can include reinforcing elements such as fibers, whisker-shapes, platelets and particulates or have laminated or fibrous monolithic geometries. The metastable interphase material is capable of undergoing a shear or stress induced zero volume or negative volume, martensitic phase transformation, which may or may not be accompanied by a crystallographic unit cell shape change. In one embodiment, the metastable interphase material includes &bgr;-cristobalite.

Abstract: A friction material comprises a fibrous reinforcement, a friction modifier and a binder. At least potassium hexatitanate fiber and potassium octatitanate fiber are used together as the fibrous reinforcement and mixed at a ratio in a range between 2 wt % and 40 wt % of the whole of the friction material as total amount. It is preferable that a mixing ratio of the potassium hexatitanate fiber to the potassium octatitanate fiber is in a range between 1:4 and 4:1 by weight percentage.

Abstract: A fiber-composite material (7) is comprised of a yarn aggregate (6) in which yarn (2A, 2B) including at least a bundle (3) of carbon fiber and a carbon component other than carbon fiber is three-dimensionally combined and integrally formed without separation from each other; and a matrix made of Si—SiC-based materials (4A, 4B, 5A, 5B) filled between the yarn (2A, 2B) adjacent to each other within the yarn aggregate (6).

Abstract: A yarn for use in a cement mortar matrix, includes a core and a multitude of staple fibers forming a layer which envelopes the core and provides an extended surface area and interstical spaces for infiltration by cement fines and hydrates. The staple fibers are spun around the core and attached to the core, and have sufficient freedom of radial movement to provide said spaces and permit ingress of cement fines and the formation of hydrates in said spaces.

Abstract: Provided is a fiberglass binder which contains a polycarboxy polymer and a polyol, with a pH of the binder being no greater than 3.5. It is further preferred that the polycarboxy polymer has a molecular weight of less than 10,000, and more preferably about 5000 or less. The binder also preferably includes a catalyst which is an alkali metal salt of a phosphorus polyol is preferably triethanolamine. The binder also preferably includes a catalyst which is an alkali metal salt of a phosphorus-containing organic acid. The resultant binder, particularly when used in preparing fiberglass products, provides minimal processing difficulties and a product with excellent recovery and rigidity.

Abstract: A fiber-composite material includes: 55-75 wt % of carbon, 1-10 wt % of silicon and 10-50 wt % of silicon carbide, and the matrices comprising Si—SiC-based materials formed integrally among assemblages of yarns comprising carbon fibers integrally formed being combined three-dimensionally so as not to separate from each other. The fiber-composite material has a coefficient of kinetic friction of 0.05-0.6 and a porosity of 0.5-10%.

Abstract: Friction linings for torque transmission devices, in particular for friction clutches, are based on an inorganic composite material of (a) a matrix of glass or glass ceramic, (b) inorganic reinforcing fibres and (c) one or more ceramic, vitreous or metallic fillers, the fillers providing the friction clutches with improved comfort characteristics.

Abstract: A wet type friction material of a layered construction is disclosed, in which at least two layers are laminated, one of the two layers being a friction-surface layer disposed on a friction-surface side, the other one thereof being a base layer disposed on a fixed side, wherein the entire friction material exhibiting a Young's modulus of Et, the base layer exhibiting a Young's modulus of Eb, and the Et and the Eb satisfying a relationship of Eb/Et<1. When the friction material slides on a mating member, it is good in the ability of following the mating member because the base layer exhibits the low Young's modulus Eb. As a result, it is possible to secure a large contact area with respect to the mating member. At the same time, it is possible to secure a high friction coefficient because the friction-surface layer exhibiting a high Young's modulus Et contacts with the mating member.

Abstract: A process for preparing pins for connecting carbon electrodes is presented. In particular, a process for preparing pins for connecting carbon electrodes including the steps of combining calcined coke, a liquid pitch binder and carbon fibers derived from mesophase pitch to form a pinstock blend; extruding the pinstock blend to form a green pinstock; baking the green pinstock to form a carbonized pinstock; and graphitizing the carbonized pinstock by maintaining the carbonized pinstock at a temperature of at least about 2500° C. for no more than about 18 hours is presented. The pins prepared by the inventive process are also presented.

Abstract: An expansion joint patch apparatus for repairing failed or torn expansion joint belting having a substantially flat, woven substrate material, and a cured solution of suspended elastomer, coating the substrate material. The substrate material is selected from the group consisting of aramid, fiberglass, corrosion resistant alloy wire, polyester, ceramic and kevlar fabrics. The elastomer material is selected from the group consisting of chloroprene, chlorosulfonated polyethylene, ethylene propylene, chloronated isobutylene isoprene, fluoroelastomers and silicone rubbers. The invention further includes a method for forming a fluoroelastomer patch for repairing fabric expansion joints.

Abstract: A Si—SiC material of Si concentration-gradient type is obtained by melt-infiltrating Si into a molded material comprising SiC particles. The Si—SiC material has a porosity of 1.0% or less and in the Si—SiC material the Si concentration decreases gradually from the surface layer towards the innermost layer. A SiC fiber-reinforced Si—SiC composite material of Si concentration-gradient type is obtained by melt-infiltrating Si into a molded material comprising a SiC fiber and SiC particles. The composite material has a porosity of 1.0% or less and in the composite material the Si concentration decreases gradually from the surface layer towards the innermost layer. These materials are significantly improved in corrosion resistance in highly oxidative and corrosive environment, strength, and healability of defects of surface layer and innermost layer.

Abstract: The material comprises fiber reinforcement made of fibers that are essentially constituted by silicon carbide, and an interphase layer between the fibers of the reinforcement and the matrix. The reinforcing fibers are long fibers containing less than 5% atomic residual oxygen and they have a modulus greater than 250 GPa, and the interphase layer is strongly bonded to the fibers and to the matrix such that the shear breaking strengths within the interphase layer and at the fiber-interphase bonds and at the interphase-matrix bonds are greater than the shear breaking strengths encountered within the matrix.

Abstract: A preform used as a reinforcement of a composite product is formed by heating a homogeneous slurry mixture of oxide type ceramic particles and/or oxide type ceramic whiskers which are reactive with magnesium (Mg) and a metal oxide having standard energy of formation equal to or less than a magnesium oxide (MgO) or an inorganic compound formed by decomposing the metal oxide to sinter the oxide type ceramic particles and/or oxide type ceramic whiskers.

Abstract: A laminated matrix composite made of a reinforcement phase and coated with several layers of a metallic, ceramic, or polymeric matrix material, the average thickness of the layers of matrix material being between 0.005 and 5 &mgr;m thick.

Abstract: An electromagnetic wave absorbing material is provided by shaping a resin composition containing 5 to 10 parts by weight of a carbon black and 1 to 10 parts by weight of a gas phase growth carbon fiber in a resin based on 100 parts by weight of the resin.

Abstract: The fiber-strengthened silicon nitride sintered substance (10) comprises silicon nitride particles (2), an oxide or nitride grain boundary phase (4) containing silicon (3), a silicon nitride layer (5) and strengthened fibers (6). Contained in the oxide or nitride grain boundary phase (4) are a crystal phase (12) containing MnSiN2, at least one element selected from the group consisting of aluminum (Al), yttrium (Y) and silicon (Si), and an amorphous phase (14) containing manganese (Mn), oxygen (O) and nitrogen (N).

Abstract: A tool for machining workpieces, specially metal workpieces, by cutting, e.g., grinding, polishing, milling, separating or honing, comprising at least one stock-removing tool portion and whose machining range consists of a composite material containing a hard material. Said tool is characterized in that the composite material is formed by a fiber structure consisting of substantially continuous fibers made of carbon and/or a ceramic material and by a matrix containing carbon and hard material, and is also characterized in that at least the machining range, like the cutting or milling tool, is made of said composite material.

Abstract: A process for producing sharp surface visible patterns on composite articles formed of resin coated reinforcing strands employs a liquid uncured resin having a coloring component therein to produce an opaque resin of light color to mask the color of the reinforcing strands. An absorbent surface veil is applied to the surface of the article before curing the resin to produce an absorbent opaque surface layer of light color into which a pattern of contrasting color is then transferred by sublimating an ink or dye pattern from a pattern carrier into the opaque resin impregnated surface layer and veil. Articles ready for application of the surface pattern thereto by sublimation may be produced using pultrusion or hand lay-up methods. Distribution of the surface pattern partially or entirely through the thickness of the surface layer results in an article having a surface in which the pattern remains sharply visible despite surface wear.

Abstract: A carbon/carbon composite in which a carbon matrix containing a controlled amount of boron or a boron compound is reinforced with carbon fiber exhibits a low coefficient of friction, i.e., on the order of 0.04 to 0.1 at temperatures up to 600° C., which is one of the lowest frictional coefficients for any type of carbonaceous material, including graphite, glassy carbon, diamond, diamond-like carbon and other forms of carbon material.

Abstract: A ceramic composite includes (a) 30 to 60% by volume of C-fibers; (b) 10 to 55% by volume of a matrix made of SiC and C, wherein the weight ratio SiC:C is in the range of between 20:1 and 2:1; (c) 5 to 40% by volume porosity that may be open or closed. A base material is formed from a)+b)+c).

Abstract: A thermal gradient resistant fiber-reinforced composite structure which has a hot operating side and an opposite cool operating side and a thickness &tgr; therebetween. In one embodiment, the composite has two regions: hot and cool. The hot region consists essentially of a fiber having a first coefficient of thermal expansion and a matrix material and the cool region consists essentially of a fiber having a second coefficient of thermal expansion and a matrix material. In this embodiment, the hot region has a thickness &tgr;H of about 10 to 90 percent of the total thickness &tgr; between the hot side and the cool side, and the cool region has a thickness &tgr;C of about 90 to 10 percent of the total thickness &tgr;. In a second embodiment, the composite has a hot operating side and an opposite cool operating side and a thickness &tgr;′ therebetween. In this embodiment, the composite has three regions: hot, intermediate and cool.

Abstract: The ceramic matrix composite is constructed by a ceramic matrix containing SiC formed by a reaction sintering as a main phase and ceramic fibers comprising SiC compounded in this matrix. A coat layer that has been previously coated on the fibers is disposed between the fiber and the matrix. The layer is provided with a BN layer with a preset thickness covering on the surface of the fiber, a C layer with a preset thickness covering the BN layer, and a SiC layer with a preset thickness covering the C layer.