Abstract: A chemical vapor deposition apparatus includes a chamber, a susceptor supporting a substrate, a backing plate to which power is applied, a diffuser providing a deposition gas, and a first insulator. The first insulator may include a first portion covering a top surface of the backing plate, and a second portion assembled with the first portion and covering a sidewall of the backing plate.

Abstract: A tackified ceramic fabric sheet includes a pre-preg layer having a fabric of woven ceramic tows and a tackifier compound surrounding the tows and comprising 15% to 60% polyvinyl butyral with ethanol. The sheet further includes a removable first backing film layer on a first side of the pre-preg layer.

Abstract: In some embodiments, a semiconductor fabrication tool is provided. The semiconductor fabrication tool includes a first processing zone having a first ambient environment and a second processing zone having a second ambient environment disposed at different location inside a processing chamber. A first exhaust port and a second exhaust port are disposed in the first and second processing zones, respectively. A first exhaust pipe couples the first exhaust port to a first individual exhaust output. A second exhaust pipe couples the second exhaust port to a second individual exhaust output, where the second exhaust pipe is separate from the first exhaust pipe. A first adjustable fluid control element controls the first ambient environment. A second adjustable fluid control element controls the second ambient environment, where the first adjustable fluid control element and the second adjustable fluid control element are independently adjustable.

Abstract: One aspect relates to a method for the manufacture of a medical electrode, including: (i) providing a substrate; (ii) applying a composition onto the substrate, wherein the composition comprises (a) a non-aqueous solvent and (b) an organic precious metal complex compound that is dissolved in the solvent; (iii) heating the composition and thereby forming a precious metal layer on the substrate, wherein the solubility of the organic precious metal complex compound in propylene glycol mono-propyl ether at 25° C. and 1013 hPa is at least 1 mass percent, or at least 2, 3, 4, 5 or 10 mass percent, in relation to the total mass of the composition.

Abstract: A process for manufacturing a ceramic matrix composite part, includes infiltrating a fibrous structure including a powder composition with a melt infiltration composition including at least silicon in order to form a ceramic matrix in the porosity of the fibrous structure, the powder composition including at least silicon carbide particles, wherein the silicon carbide particles have a bimodal size distribution with a first set of silicon carbide particles having a first average size and a second set of silicon carbide particles having a second average size smaller than the first average size, the number of particles in the first set being greater than the number of particles in the second set.

Abstract: Methods of forming a carbon fiber reinforced carbon foam are provided. Such a method may comprise heating a porous body composed of a solid material comprising covalently bound carbon atoms and heteroatoms and having a surface defining pores distributed throughout the solid material, in the presence of an added source of gaseous hydrocarbons. The heating generates free radicals in the porous body from the heteroatoms and induces reactions between the free radicals and the gaseous hydrocarbons to form covalently bound carbon nanofibers extending from the surface of the solid material and a network of entangled carbon microfibers within the pores the porous body, thereby forming a carbon fiber reinforced carbon foam. Carbon fiber reinforced carbon foams and ballistic barriers incorporating the foams are also provided.

Abstract: This innovation provides for a revolutionary advancement in the area of very thick and very high thermal conductivity carbon-carbon (C—C) composites for both commercial and military. Novel, surface treated to achieve desired chemistry, exhibiting no agglomeration, carbon-based fillers are used enabling stable slurries up to 45 wt % solids to be used in the composite pre-pregging for 1-D and 2-D, 2-5 D and 3-D preforms infiltration. The need for carbonization is eliminated. No closed porosity C—C composites are produced. Up to 12? thick C—C composites with no density gradient and thermal conductivity in excess of 650 W/mK were fabricated via chemically induced graphitization.

Abstract: A method (100) of cooling a deposition source (200) is described. The method includes stopping (110) depositing material from the deposition source, the deposition source being arranged in a deposition chamber (250), and introducing (120) a cooling gas into the deposition chamber (250), the cooling gas comprising a thermal conductivity ? of ??0.05 [W/(m*K)]. Further, a chamber for cooling a deposition source is described. The chamber includes a deposition source being arranged in the chamber. Further, the chamber includes a cooling gas supply system configured for providing a cooling gas into the chamber, the cooling gas comprising a thermal conductivity ? of ??0.05 [W/(m*K)].

Abstract: A method of producing a ceramic matrix composite including a protective ceramic coating thereon comprises applying a surface slurry onto an outer surface of an impregnated fiber preform. The surface slurry includes particulate ceramic solids dispersed in a flowable preceramic polymer comprising silicon, and the impregnated fiber preform comprises a framework of ceramic fibers loaded with particulate matter. The flowable preceramic polymer is cured, thereby forming on the outer surface a composite layer comprising a cured preceramic polymer with the particulate ceramic solids dispersed therein. The cured preceramic polymer is then pyrolyzed to form a porous ceramic layer comprising silicon carbide, and the impregnated fiber preform and the porous ceramic layer are infiltrated with a molten material comprising silicon. After infiltration, the molten material is cooled to form a ceramic matrix composite body with a protective ceramic coating thereon.

Abstract: A method of manufacturing a coated reinforcing fiber for use in Ceramic Matrix Composites, the method comprising pre-oxidizing a plurality of silicon-based fibers selected from the group consisting of silicon carbide (SiC) fibers, silicon nitride (Si3N4) fibers, SiCO fibers, SiCN fibers, SiCNO fibers, and SiBCN fibers at between 700 to 1300 degrees Celsius in an oxidizing atmosphere to form a silica surface layer on the plurality of silicon-based fibers, forming a plurality of pre-oxidized fibers; applying a rare earth orthophosphate (REPO4) coating to the plurality of pre-oxidized fibers; and heating the plurality of REPO4 coated pre-oxidized fibers at about 1000-1500 degrees Celsius in an inert atmosphere to react the REPO4 with the silica surface layer to form a rare earth silicate or disilicate. The pre-oxidizing step may be 0.5 hours to about 100 hours. The heating step may be about 5 minutes to about 100 hours.

Abstract: A method of producing a film having excellent external quantum efficiency when used in a light emitting layer of a light emitting device is provided. A method of film production includes preparing an ink containing a specific metal complex, storing the ink for 3 days or more under light shielding, and forming a film by using the stored ink. The total content of metal complexes having a molecular weight larger by 16, 32 or 48 than that of the specific metal complex according to an area percentage value determined by liquid chromatography is 0.6 or less when the content of the specific metal complex is taken as 100.

Abstract: A method of depositing silicon carbide on a preform to form a ceramic matrix composite comprises placing the preform into a reaction vessel, removing air from the reaction vessel and backfilling the reaction vessel with an inert gas to an operating pressure. The reaction vessel and the preform are heated to an operating temperature. A carrier gas and precursor materials are heated to a preheat temperature outside of the reaction vessel. The carrier gas and the precursor materials are introduced to the reaction vessel in a specified ratio. Off gasses, the precursor materials that are unspent, and the carrier gas are removed from the reaction vessel to maintain the specified ratio of the precursor materials in the reaction vessel.

Abstract: A system and method of melt infiltrating components is provided. In one example aspect, an inductive heating system includes a heating source that inductively heats a susceptor. The susceptor defines a working chamber in which components can be received. During melt infiltration, the system can heat the susceptor and thus the components and melt infiltrants disposed within the working chamber at a first heating rate. The first heating rate can be faster than 50° C./minute. The system can then heat the components and melt infiltrants at a second heating rate. The first heating rate is faster than the second heating rate. Thereafter, the system can heat the components and infiltrants at a third heating rate. The third heating rate can be a constant rate at or above the melting point of the melt infiltrants. The infiltrants can melt and thus infiltrate into the component to densify the component.

Abstract: A method for manufacturing a part made of composite material in which an adhesion promoter is grafted to a coating present on the fibre surface as well as to a ceramic precursor resin. Afterwards, a ceramic matrix phase is formed in the porosity of the fibre preform by pyrolysis of the polymerised resin.

Abstract: A method for manufacturing a part made of composite material includes forming a ceramic matrix phase in pores of a fibrous preform by pyrolysis of a cross-linked copolymer ceramic precursor, the cross-linked copolymer including a first precursor macromolecular chain of a first ceramic having free carbon, and a second precursor macromolecular chain of a second ceramic having free silicon, the first macromolecular chain being bonded to the second macromolecular chain by cross-linking bridges including a bonding structure of formula *1—X—*2; in this formula, X designates boron or aluminium, -*1 designates the bond to the first macromolecular chain and -*2 the bond to the second macromolecular chain.

Abstract: A ceramic article includes a ceramic matrix composite that has a porous reinforcement structure and a ceramic matrix within pores of the porous reinforcement structure. The ceramic matrix composite includes a surface zone comprised of an exterior surface of the ceramic matrix composite and pores that extend from the exterior surface into the ceramic matrix composite. A glaze material seals the surface zone within the pores of the surface zone and on the exterior surface of the surface zone as an exterior glaze layer on the ceramic matrix composite. The glaze material is a glass or glass-ceramic material. The ceramic matrix composite includes an interior zone under the surface zone, and the interior zone is free of any of the glaze material and has a greater porosity than the surface zone.

Abstract: A method of making a ceramic matrix composite (CMC) that may show improved resistance to chemical attack from molten silicon along with excellent mechanical strength is described. The method includes forming an interphase coating on one or more silicon carbide fibers, depositing a matrix layer comprising silicon carbide on the interphase coating, oxidizing the matrix layer to form an oxidized film comprising silicon oxide, depositing a wetting layer comprising silicon carbide on the oxidized film. After depositing the wetting layer, a fiber preform containing the silicon carbide fibers is heat treated. After the heat treatment, the fiber preform is infiltrated with a slurry. After infiltration with the slurry, the fiber preform is infiltrated with a melt containing silicon, and then the melt is cooled to form a ceramic matrix composite.

Abstract: A metal complex is disclosed. In an embodiment a metal complex includes at least one metal atom M and at least one ligand L attached to the metal atom M, wherein the ligand L has the following structure: wherein E1 and E2 are oxygen, wherein the substituent R1 is selected from the group consisting of branched or unbranched, fluorinated aliphatic hydrocarbons with 1 to 10 C atoms, wherein n=1 to 5, wherein the substituent R2 is selected from the group consisting of branched or unbranched aliphatic hydrocarbons with 1 to 10 C atoms, aryl and heteroaryl, wherein m>0 to at most 5?n, and wherein the metal M is a main group metal of groups 13 to 15 of the periodic table of elements.

Abstract: A method for forming an ultra-high temperature (UHT) composite structure includes dispensing a first polymeric precursor with a spinneret; forming a first plurality of nanofibers from the first polymeric precursor; depositing the first plurality of nanofibers with a collector; and applying a fluid, with a nozzle, onto the first plurality of nanofibers disposed on the collector. The fluid includes a second polymeric precursor.

Abstract: A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.