Abstract

An exhaust trap configured to filter an exhaust stream of a vacuum furnace may include a housing and a media barrier. The housing defines an interior. The media barrier may divide the interior of the housing into a first chamber and a second chamber and is configured to allow the exhaust stream to flow from the first chamber to the second chamber. The exhaust trap may further include a filter medium in the first chamber and configured to filter the exhaust stream. No filter medium is present in the second chamber.

IPC Classes  ?

• F01N 3/022 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust by means of filters characterised by specially adapted filtering structure, e.g. honeycomb, mesh or fibrous

Abstract

A test apparatus for a ceramic matrix composite (CMC) component. The test apparatus includes a first support member configured to mechanically support a CMC component from a first side. The CMC component includes a T-joint and a pinhole. The test apparatus includes a second support member configured to mechanically support the CMC component from a second side opposite the first side. The first support member and the second support member are configured to be forced toward each other to cause the CMC component to fail at the pinhole and not at the T-joint.

IPC Classes  ?

• G01N 3/08 - Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces

Abstract

An assembly for nuclear applications includes a tubular cladding for containing nuclear fuel. The tubular cladding comprises a ceramic matrix composite. An assembly tube surrounds the tubular cladding, and a collar is positioned between the tubular cladding and the assembly tube. The collar extends circumferentially around the cladding and comprises the ceramic matrix composite. The tubular cladding may be centered within the assembly tube by the collar.

IPC Classes  ?

• G21C 21/02 - Manufacture of fuel elements or breeder elements contained in non-active casings
• G21C 3/07 - CasingsJackets characterised by their material, e.g. alloys

Abstract

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

A machining system includes a blade assembly, a first shaft configured to rotate in a first direction, and a second shaft configured to rotate in a second direction that is opposite the first direction. The blade assembly includes a blade, a circular aperture, and an ovular aperture. The first shaft includes a first cam disposed within the circular aperture. The second shaft includes a second cam disposed within the ovular aperture. The first cam and the second cam are configured to move the blade assembly in a circular motion.

IPC Classes  ?

• B28D 1/22 - Working stone or stone-like materials, e.g. brick, concrete, not provided for elsewhereMachines, devices, tools therefor by cutting, e.g. incising
• B28D 7/02 - Accessories specially adapted for use with machines or devices of the other groups of this subclass for removing or laying dust, e.g. by spraying liquidsAccessories specially adapted for use with machines or devices of the other groups of this subclass for cooling work

Abstract

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A method of forming a ceramic matrix composite having a smooth surface includes laying up a plurality of plies, where some or all of the plies include an arrangement of spread tows comprising carbon fibers, thereby forming a fiber preform. Each spread tow has a height-to-width aspect ratio of less than about 0.1. The fiber preform is infiltrated with a ceramic matrix material and/or ceramic matrix precursor to embed the carbon fibers in a ceramic matrix. Thus, a ceramic matrix composite comprising a smooth and/or flat surface devoid of undulations from rounded tows is formed.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching

Abstract

A method to form a machinable ceramic matrix composite comprises forming a porous ceramic multilayer on a surface of a fiber preform. In one example, the porous ceramic multilayer comprises a gradient in porosity in a direction normal to the surface. In another example, the porous ceramic multilayer includes low-wettability particles having a high contact angle with molten silicon, where an amount of the low-wettability particles in the porous ceramic multilayer varies in a direction normal to the surface. After forming the multilayer, the fiber preform is infiltrated with a melt, and the melt is cooled to form a ceramic matrix composite with a surface coating thereon. An outer portion of the surface coating is machined to form a ceramic matrix composite having a machined surface with a predetermined surface finish and/or dimensional tolerance.

IPC Classes  ?

• B32B 37/20 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of continuous webs only
• B32B 18/00 - Layered products essentially comprising ceramics, e.g. refractory products

Abstract

In various aspects, a preheater, a directed flow chemical vapor infiltration/chemical vapor deposition (CVI/CVD) furnace, and/or an installation jig are described. In one example, a preheater includes a central inlet; a circuitous gas flow path downstream of the central inlet; a plenum section downstream of the circuitous gas flow path; and an outlet diffuser plate defining a plurality of apertures fluidly configured to couple the preheater to a furnace working zone, wherein the outlet diffuser plate is downstream of the plenum section, wherein the circuitous gas flow path is fluidly coupled to the plenum section by an outer circumferential slot opening.

IPC Classes  ?

• F27B 14/08 - Details specially adapted for crucible, pot or tank furnaces
• F27B 14/12 - Covers therefor

Abstract

A method of producing or repairing a fiber-reinforced ceramic matrix composite comprises delivering a powder composition comprising SiC particles and chopped coated SiC fibers into or onto a powder receptacle configured for composite fabrication or repair. After delivering the powder composition into or onto the powder receptacle, the SiC particles are densified to form a SiC matrix reinforced with the chopped coated SiC fibers, thereby producing or repairing a fiber-reinforced ceramic matrix composite.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/64 - Burning or sintering processes
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/87 - Ceramics

Abstract

In various aspects, a preheater, a directed flow chemical vapor infiltration/chemical vapor deposition (CVI/CVD) furnace, and/or an installation jig are described. In one example, a preheater includes a central inlet; a circuitous gas flow path downstream of the central inlet; a plenum section downstream of the circuitous gas flow path; and an outlet diffuser plate defining a plurality of apertures fluidly configured to couple the preheater to a furnace working zone, wherein the outlet diffuser plate is downstream of the plenum section, wherein the circuitous gas flow path is fluidly coupled to the plenum section by an outer circumferential slot opening.

IPC Classes  ?

• C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
• C23C 16/46 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for heating the substrate

Abstract

In some examples, a multilevel retort assembly. The assembly includes a base defining a base perimeter; and a plurality of shells. Each shell has a diffuser plate support and a perimeter with a substantially similar shape as the base perimeter. The plurality of shells are stacked on each other, mechanically supported by the base, and surround an inner retort volume. The at least one shell of the plurality of shells defines a removable window. The assembly also includes a plurality of diffuser plates, each diffuser plate supported by a corresponding diffuser plate support of the plurality of diffuser plate supports.

IPC Classes  ?

• F27B 5/02 - Muffle furnacesRetort furnacesOther furnaces in which the charge is held completely isolated of multiple-chamber type
• F27B 5/12 - Arrangement of devices for charging
• F27D 5/00 - Supports, screens or the like for the charge within the furnace

Abstract

In various aspects, a preheater, a directed flow chemical vapor infiltration/chemical vapor deposition (CVI/CVD) furnace, and/or an installation jig are described. In one example, a preheater includes a central inlet; a circuitous gas flow path downstream of the central inlet; a plenum section downstream of the circuitous gas flow path; and an outlet diffuser plate defining a plurality of apertures fluidly configured to couple the preheater to a furnace working zone, wherein the outlet diffuser plate is downstream of the plenum section, wherein the circuitous gas flow path is fluidly coupled to the plenum section by an outer circumferential slot opening.

IPC Classes  ?

• C23C 16/40 - Oxides
• C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
• C23C 16/46 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for heating the substrate
• F27B 5/04 - Muffle furnacesRetort furnacesOther furnaces in which the charge is held completely isolated adapted for treating the charge in vacuum or special atmosphere

Abstract

Methods of pressure assisted melt infiltration of fiber preforms are provided. The fiber preform is provided inside of a pressure vessel. The pressure vessel projects into a molten material contained in a crucible. The pressure vessel has an opening located below a surface of the molten material through which the molten material enters the pressure vessel. An end of the fiber preform contacts the molten material within the pressure vessel. The pressure vessel and crucible are located in a furnace. The molten material is pulled within the pressure vessel by increasing a first pressure at a first port of the furnace so the first pressure is higher than a second pressure at a second port of the pressure vessel. The second port is located above the molten material located within the pressure vessel. The fiber preform is infiltrated with the molten material.

IPC Classes  ?

• B22F 7/08 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder

Abstract

In some examples, a slurry infiltration fixture. The infiltration fixture includes a fixture main body that includes a slurry introduction channel and a plurality of fixture walls defining a cavity configured to receive a porous component. The cavity includes a component volume and a reservoir volume. The plurality of fixture walls includes a shape configured to define a fixed offset between the porous component and the plurality of fixture walls and a fixed volume for slurry between the plurality of fixture walls and the porous component. The slurry introduction channel is configured introduce the slurry into the cavity through an opening proximate a bottom of the cavity.

IPC Classes  ?

• C04B 35/628 - Coating the powders
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like

Abstract

A method of forming an aperture in a ceramic matrix composite material is provided. The method may comprise drilling a pilot hole into the ceramic matrix composite material and spiral machining the pilot hole to enlarge a diameter of the pilot hole, wherein the enlarged pilot hole is the aperture in the ceramic matrix composite material. The method may comprise spiral machining the pilot hole in a radial direction with a tool to enlarge a diameter of the pilot hole until the aperture in the ceramic matrix composite material is formed. The tool may have a first diameter in a section of the tool and a second diameter on either side of the section of the tool or on both sides of the section of the tool, wherein the second diameter is larger than the first diameter.

IPC Classes  ?

• B23B 35/00 - Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machinesUse of auxiliary equipment in connection with such methods
• B23B 51/00 - Tools for drilling machines
• B23B 51/10 - Bits for countersinking

Abstract

A method to produce a ceramic matrix composite part, wherein the method comprises providing a ceramic fiber preform. Wherein the ceramic fiber preform includes a three-dimensional framework of a plurality of ceramic fibers. The method comprising, prior to melt infiltration, adding a layer of machinable stock to a target area of the ceramic fiber preform, melt infiltrating the ceramic fiber preform, forming the ceramic matrix composite part by cooling the melt infiltrated ceramic fiber preform, and machining the part in the target area where the machinable stock is located.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/628 - Coating the powders

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.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/65 - Reaction sintering of free metal- or free silicon-containing compositions

Abstract

A turbine shroud segment for use in a gas turbine engine includes a ceramic shroud segment formed to define a circumferentially extending channel that opens radially inwardly and a layer of abradable material that extends axially along a radial inner surface of the ceramic shroud segment to provide a flow path surface of the turbine shroud segment.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

Abstract

A turbine shroud assembly for a gas turbine engine includes a shroud wall extending circumferentially partway around a central reference axis to define a gas path of the gas turbine engine. An attachment feature extends radially from the shroud wall. A foam is located at least on the shroud wall.

IPC Classes  ?

• F01D 25/14 - Casings modified therefor
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/14 - Form or construction
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades

Abstract

In some examples, a method including forming a layer of a slurry composition between a first ceramic or CMC part and a second ceramic or CMC part. The slurry composition includes a carrier material; and a plurality of solid particles in the carrier material. The plurality of solid particles includes first silicon carbide (SiC) particles defining a first average particle size, second SiC particles defining a second average particles size that is less than the first average particles size, and reactive additive particles. The method includes heating the layer of slurry composition to react the plurality of reactive additive particles to fuse the plurality of first SiC particles and the plurality of second SiC particles together with the reactive additive particles, wherein the fused layer of the slurry composition forms a joint layer that joins the first ceramic or CMC part to the second ceramic or CMC part.

IPC Classes  ?

• C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating

Abstract

An airfoil assembly for a gas turbine engine includes an airfoil extending radially relative to a central reference axis. A spar is located within the airfoil and spaced from the airfoil at all radial locations along the airfoil such that a gap is maintained between the airfoil and the spar. A foam is located between the airfoil and the spar.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/14 - Form or construction

Abstract

A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/45 - Coating or impregnating
• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

In some examples, the disclosure describes an article and a method of making the same that includes a substrate defining an outer surface, a barrier layer on the outer surface of the substrate, the barrier layer defining a textured surface having a plurality of cells, each cell having a geometry and a depth, and an overlying layer formed on the textured surface of the barrier layer. The barrier layer may be configured to reduce migration of material from the substrate to the overlaying layer to reduce or prevent formation of cristobalite phase thermally grown oxide.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A method to form a machinable ceramic matrix composite comprises forming a porous ceramic multilayer on a surface of a fiber preform. In one example, the porous ceramic multilayer comprises a gradient in porosity in a direction normal to the surface. In another example, the porous ceramic multilayer includes low-wettability particles having a high contact angle with molten silicon, where an amount of the low-wettability particles in the porous ceramic multilayer varies in a direction normal to the surface. After forming the porous ceramic multilayer, the fiber preform is infiltrated with a melt, and the melt is cooled to form a ceramic matrix composite with a surface coating thereon. An outer portion of the surface coating is more readily machinable than an inner portion of the surface coating. The outer portion of the surface coating is machined to form a ceramic matrix composite having a machined surface with a predetermined surface finish and/or dimensional tolerance.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/628 - Coating the powders
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C04B 35/64 - Burning or sintering processes
• F01D 5/14 - Form or construction
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

A method of making a ceramic matrix composite that exhibits chemical resistance has been developed. The method comprises depositing a compliant layer comprising boron nitride, silicon-doped boron nitride, and/or pyrolytic carbon on silicon carbide fibers, depositing a barrier layer having a high contact angle with molten silicon on the compliant layer, and depositing a wetting layer comprising silicon carbide, boron carbide, and/or pyrolytic carbon on the barrier layer. After depositing the wetting layer, a fiber preform comprising the silicon carbide fibers is infiltrated with a slurry. After slurry infiltration, the fiber preform is infiltrated with a melt comprising silicon, and then the melt is cooled, thereby forming a ceramic matrix composite.

IPC Classes  ?

• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/87 - Ceramics
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials

Abstract

A method of making a ceramic matrix composite that exhibits moisture and environmental resistance has been developed. The method includes depositing a diffusion barrier layer comprising boron nitride on silicon carbide fibers and depositing a moisture-tolerant layer comprising silicon-doped boron nitride on the diffusion barrier layer, where a thickness of the moisture-tolerant layer is from about 3 to about 300 times a thickness of the diffusion barrier layer. Thus, a compliant multilayer including the moisture-tolerant layer and the diffusion barrier layer is formed. A wetting layer comprising silicon carbide, boron carbide, and/or pyrolytic carbon is deposited on the compliant multilayer layer. After depositing the wetting layer, a fiber preform comprising the silicon carbide fibers is infiltrated with a slurry. After slurry infiltration, the fiber preform is infiltrated with a melt comprising silicon and then the melt is cooled, thereby forming a ceramic matrix composite.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/65 - Reaction sintering of free metal- or free silicon-containing compositions

Abstract

An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment that is supported by the carrier relative to a high temperature zone. The blade track segment provides a heat shield for use in high temperature applications protecting the carrier and other components.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

Abstract

A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

In some examples, a method may include depositing, from a slurry comprising particles including silicon metal, a bond coat precursor layer including the particles comprising silicon metal directly on a ceramic matrix composite substrate. The method also may include locally heating the bond coat precursor layer to form a bond coat comprising silicon metal. Additionally, the method may include forming a protective coating on the bond coat. In some examples, an article may include a ceramic matrix composite substrate, a bond coat directly on the substrate, and a protective coating on the bond coat. The bond coat may include silicon metal and a metal comprising at least one of Zr, Y, Yb, Hf, Ti, Al, Cr, Mo, Nb, Ta, or a rare earth metal.

IPC Classes  ?

• B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
• B32B 17/06 - Layered products essentially comprising sheet glass, or fibres of glass, slag or the like comprising glass as the main or only constituent of a layer, next to another layer of a specific substance
• C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating
• C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C23C 20/04 - Coating with metallic material with metals
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/85 - Coating or impregnating with inorganic materials
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/52 - Multiple coating or impregnating

Abstract

A method comprises inspecting a ceramic matrix composite component assembled in a gas turbine engine to determine an extent of damage to the ceramic matrix composite component, determining a repair technique to repair the damage to the ceramic matrix composite component based on the extent of damage to the ceramic matrix composite component, and repairing the ceramic matrix composite component using the repair technique.

IPC Classes  ?

• B23P 6/00 - Restoring or reconditioning objects
• F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

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.

IPC Classes  ?

• B32B 18/00 - Layered products essentially comprising ceramics, e.g. refractory products
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 41/52 - Multiple coating or impregnating
• C04B 35/571 - Fine ceramics obtained from polymer precursors
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 35/52 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbon, e.g. graphite
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/515 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides
• C04B 35/76 - Fibres, filaments, whiskers, platelets, or the like
• C04B 38/06 - Porous mortars, concrete, artificial stone or ceramic warePreparation thereof by burning-out added substances

Abstract

A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/14 - Form or construction
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• C04B 35/64 - Burning or sintering processes

Abstract

A turbine section of a gas turbine engine includes a vane assembly that redirects hot gases in the turbine section, a turbine shroud that extends around a turbine wheel to keep the hot gases from avoiding interaction with the turbine wheel, and a heat shield that provides parts of the vane assembly and the turbine shroud. The heat shield comprises ceramic matrix composite materials and is formed as a one piece component. The heat shield includes a vane portion that protects other vane assembly parts, a seal segment portion that protects other turbine shroud parts, and a forward turn-up and an aft turn-up. The forward turn-up and the aft turn-up couple the heat shield to other parts of the turbine section.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a supported component, illustratively used as a heat shield. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

The disclosure describes braze tape coatings and technique to form articles with differing physical properties in different layers or regions of the article. An example method includes forming a braze tape defining at least one layer that includes a first segment and a second segment. A portion of the second segment in the plane is adjacent to a portion of the first segment in a plane of the layer. The method also includes positioning the braze tape on a surface of a substrate, the plane of the layer of the braze tape being parallel to the surface of the substrate. The method also includes heating the braze tape to melt a constituent of at least one of the first coating material and the second coating material to form a densified coating on the surface of the substrate.

IPC Classes  ?

• C04B 41/52 - Multiple coating or impregnating
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/87 - Ceramics
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions

Abstract

A component for use in a gas turbine engine includes a component body, and a damage-indicative coating. The damage-indicative coating is configured to change from an intact state in which the damage-indicative coating has a first appearance to a damaged state in which the damage-indicative coating has a second appearance.

IPC Classes  ?

• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
• F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants

Abstract

A method of producing a melt infiltrated ceramic matrix composite (CMC) article that includes the steps of: forming a ceramic fiber preform; optionally, rigidizing the ceramic fiber preform with a fiber interphase coating via a Chemical Vapor Infiltration (CVI) process, infiltrating a ceramic slurry into the porous body or preform, conducting one or more secondary operations, and finally, melt infiltrating the preform with molten silicon or a silicon alloy to form the CMC article. The infiltration of a ceramic slurry into a ceramic fiber preform to form a green body is performed along with the use of convection and/or conduction as heat transfer mechanisms, such that the ceramic slurry does not require the incorporation of a pre-gelation material in order for the slurry to remain within the green body during subsequent processing steps.

IPC Classes  ?

• C04B 41/52 - Multiple coating or impregnating
• C04B 35/628 - Coating the powders
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/51 - Metallising

Abstract

A method of producing a CMC component that includes forming a preform having a plurality of ceramic fiber plies with each ply occupying a predetermined position; rigidizing the preform with a fiber interphase coating; inspecting the preform to determine which of the plies has partially or fully delaminated; reworking the delaminated plies in the preform; infiltrating a ceramic slurry into the preform to form a green body; optionally, conducting a secondary operation on the green body; and infiltrating the green body with a molten silicon or silicon alloy to form the CMC component. The step of reworking delaminated plies may also be applied to a green body formed after ceramic slurry infiltration into a rigidized fiber preform.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/657 - Processes involving a melting step for manufacturing refractories

Abstract

A method is provided in which a first tape is applied to an outer surface of a ceramic matrix composite (CMC). A second tape is applied to the first tape. The second tape is heated to at least a melting temperature of the second tape. During heating, the first tape is infiltrated with a molten material from the second tape, which forms a surface layer on the CMC.

IPC Classes  ?

• C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/87 - Ceramics

Abstract

A turbine shroud segment of a gas turbine engine includes a carrier segment, a blade track segment, and a plurality of seals arranged between the carrier segment and the blade track segment. The plurality of seals are arranged between the carrier segment and the blade track segment to block gases from passing between the carrier segment and the blade track segment.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gases from passing over turbine blades included in the gas turbine engine.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

A method of infiltrating a fiber preform comprises positioning an assembly in a process chamber, where the assembly includes a tool comprising through-holes, a fiber preform constrained within the tool, and a sacrificial preform disposed between the fiber preform and the tool. The sacrificial preform is gas permeable. The process chamber is heated, and gaseous reactants are delivered into the process chamber during the heating. The gaseous reactants penetrate the through-holes of the tool and infiltrate the sacrificial preform and the fiber preform. Deposition of reaction products occurs on exposed surfaces of the fiber preform and the sacrificial preform, and a coating is formed thereon. In addition, the sacrificial preform accumulates excess coating material formed from increased reactions at short diffusion depths. Accordingly, the coating formed on the fiber preform exhibits a thickness variation of about 10% or less throughout a volume of the fiber preform.

IPC Classes  ?

• C04B 35/628 - Coating the powders
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 40/00 - Processes, in general, for influencing or modifying the properties of mortars, concrete or artificial stone compositions, e.g. their setting or hardening ability
• C23C 16/04 - Coating on selected surface areas, e.g. using masks
• C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber

Abstract

A method is provided in which a resin coating is applied to a surface of a preform. The resin coating includes a carbonaceous resin and a particulate. The preform is added to a tooling. The preform, which is positioned in the tooling, is cured. The tooling is removed. The resin coating on the surface of the preform is pyrolyzed to form a resin carbon-char layer on the surface of the preform. The preform and the resin carbon-char layer are infiltrated with silicon to form a ceramic matrix composite (CMC) component including a layer of silicon carbide. During the infiltration, the silicon reacts with carbon in the resin carbon-char layer to form the layer of silicon carbide on the preform.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• F01D 25/08 - CoolingHeatingHeat insulation
• C04B 35/628 - Coating the powders
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/87 - Ceramics
• B28B 11/04 - Apparatus or processes for treating or working the shaped articles for coating

Abstract

Methods of reducing dry crack formation in ceramic matrix composite green bodies are provided. Some of the methods expose the green body to a gaseous atmosphere at a relatively high humidity for a first period, and then slowly lower the humidity over a second period, where the gaseous atmosphere is at room temperature for both periods. Other methods start the gaseous atmosphere at room temperature and then raise the temperature to a higher temperature while the humidity is relatively high, and hold that temperature even as the humidity is lowered in the second period.

IPC Classes  ?

• B28B 11/24 - Apparatus or processes for treating or working the shaped articles for curing, setting or hardening
• C04B 35/64 - Burning or sintering processes

Abstract

A method to produce a protective surface layer having a predetermined topography on a ceramic matrix composite is described. The method includes applying a slurry layer to a surface of a fiber preform, and drying the slurry layer to form a particulate layer. A surface of the particulate layer is machined to improve surface smoothness and to form a machined surface. A ceramic tape is attached to the machined surface, and a tool comprising one or more features to be imprinted is placed on the ceramic tape, thereby forming a compression assembly. Heat and pressure are applied to the compression assembly to consolidate and bond the ceramic tape to the machined surface, while the one or more features of the tool are imprinted. Thus, a protective surface layer having a predetermined topography is formed.

IPC Classes  ?

• C04B 41/87 - Ceramics
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/45 - Coating or impregnating
• C04B 35/83 - Carbon fibres in a carbon matrix
• C04B 35/645 - Pressure sintering

Abstract

A method of forming a barrier layer on a ceramic matrix composite (CMC) is described. The method includes forming a particulate surface layer comprising silicon particles on an outer surface of a fiber preform. The particulate surface layer is nitrided to convert the silicon particles to silicon nitride particles. After the nitriding, the fiber preform and the particulate surface layer are infiltrated with a molten material comprising silicon. Following infiltration, the molten material is cooled, thereby forming a ceramic matrix composite with a barrier layer thereon, where the barrier layer comprises silicon nitride and less than 5 vol. % free silicon. The barrier layer may also include silicon carbide and/or one or more refractory metal silicides.

IPC Classes  ?

• C04B 35/78 - Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials

Abstract

A method for infiltrating a porous preform for a gas turbine engine is provided, which comprises providing a chamber for infiltrating a porous preform. The porous preform is positioned within a slurry confinement fixture within the chamber. A vacuum is created in the chamber. A solvent is added to the slurry confinement fixture until a pressure in the chamber is substantially equal to an equilibrium partial pressure of the solvent. A slurry is added to the slurry confinement fixture. The slurry includes the solvent and a particulate. The pressure in the chamber is increased, and the slurry is urged into the porous preform.

IPC Classes  ?

• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/45 - Coating or impregnating
• B28B 13/02 - Feeding the unshaped material to moulds or apparatus for producing shaped articles
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A method of altering a surface of a ceramic matrix composite to aid in nodule removal is described. A fiber preform comprising a framework of ceramic fibers is heated to a temperature at or above a melting temperature of silicon. During the heating, the fiber preform is infiltrated with a molten material comprising silicon. After the infiltration, the fiber preform is cooled, and the infiltrated fiber preform is exposed to a gas comprising nitrogen during cooling. Silicon nitride may be formed by a reaction of free (unreacted) silicon at or near the surface of the infiltrated fiber preform with the nitrogen. Thus, a ceramic matrix composite having a surface configured for easy nodule removal is formed. Any silicon nodules formed on the surface during cooling may be removed without machining or heat treatment.

IPC Classes  ?

• C04B 41/51 - Metallising
• C04B 41/87 - Ceramics
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials

Abstract

A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type

Abstract

A method may include depositing, from a slurry, suspension, or tape, on a surface of an additively manufactured component comprising a metal or alloy, powder comprising at least one of a metal, an alloy, or a ceramic; sintering the powder to form a surface layer on the additively manufactured component; and hot isostatic pressing the additively manufactured component and the surface layer.

IPC Classes  ?

• B22F 3/15 - Hot isostatic pressing
• B22F 1/05 - Metallic powder characterised by the size or surface area of the particles
• B22F 10/18 - Formation of a green body by mixing binder with metal in filament form, e.g. fused filament fabrication [FFF]
• B22F 10/60 - Treatment of workpieces or articles after build-up
• B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
• B28B 1/00 - Producing shaped articles from the material
• B33Y 10/00 - Processes of additive manufacturing

Abstract

An electrophoretic deposition method of forming a boron nitride (BN) nanotube interface coating on ceramic fibers has been developed. The method comprises immersing first and second electrodes in a suspension including surface-modified BN nanotubes, where the first electrode includes ceramic fibers positioned on a surface thereof. The surface-modified BN nanotubes comprise BN nanotubes with an electrically charged polymer adsorbed on surfaces thereof. A voltage is applied to the first and second electrodes, and the surface-modified BN nanotubes move toward the first electrode and deposit on the ceramic fibers. After the deposition of the surface-modified BN nanotubes, the ceramic fibers are removed from the suspension and heat treated. Accordingly, a BN nanotube interface coating is formed on the ceramic fibers.

IPC Classes  ?

• C04B 35/628 - Coating the powders
• C04B 41/45 - Coating or impregnating
• C25D 9/04 - Electrolytic coating other than with metals with inorganic materials
• C04B 35/622 - Forming processesProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products

Abstract

A turbine vane comprising ceramic matrix composite materials. The turbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

A bladed disk preform system is provided. Multiple sheets are formed or provided. Each of the sheets may include multiple ceramic fibers. Slots may be cut in each of the sheets before or after forming. The slots extend from an outer edge of the sheets inward toward a center of the sheets. The sheets are stacked on top of each other to form a bladed disk preform. The bladed disk preform is porous. The bladed disk preform may include a plurality of blade portions extending outward from a root portion. Each of the slots is positioned between adjacent blade portions.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/34 - Rotor-blade aggregates of unitary construction
• F01D 5/14 - Form or construction

Abstract

The disclosure describes a method for forming a surface layer of a ceramic matrix composite (CMC) article. The technique includes depositing a slurry on a surface of an infiltrated CMC. The slurry includes a carrier material, a binder, a plasticizer, and solid particles. The solid particles include a plurality of fine ceramic particles defining a fine particle average size less than about 5 micrometers. The method further includes drying the slurry to form an article having an outer surface layer that includes the solid particles on the infiltrated CMC. The method further includes machining at least a portion of the outer surface layer of the article. The method further includes infiltrating the article with a molten infiltrant to form a composite article.

IPC Classes  ?

• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/52 - Multiple coating or impregnating
• C04B 41/83 - Macromolecular compounds
• C04B 41/87 - Ceramics
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C04B 35/634 - Polymers
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/628 - Coating the powders
• C04B 41/48 - Macromolecular compounds

Abstract

A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a vane. The support strut is made of metallic materials. The vane is made of composite materials and is arranged around the support strut to insulate the metallic materials of the support strut during use of the turbine vane assembly.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 5/22 - Blade-to-blade connections, e.g. by shrouding
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A fluid conduit may be provided comprising a ceramic matrix composite (CMC) cross-over tube and a flange. The CMC cross-over tube may comprise a first end configured to extend into a first combustor liner of a gas turbine engine, and a second end configured to extend into a second combustor liner of a gas turbine engine. The interior of the CMC cross-over tube may define a passageway. The flange may extend outwardly from an outer surface of the CMC cross-over tube. The flange may be configured to engage at least one of the first combustor liner and the second combustor liner.

IPC Classes  ?

• F23R 3/48 - Flame tube interconnectors, e.g. cross-over tubes
• F16L 49/04 - Flanged joints

Abstract

A method of fabricating cooling features on a CMC component may comprise compressing a fabric preform within tooling including holes and/or recesses facing the fabric preform. During the compression, portions of the fabric preform are pushed into the holes and/or recesses. Gases are delivered through the tooling to deposit a matrix material on exposed surfaces of the fabric preform while the fabric preform is being compressed. The matrix material builds up on the portions of the fabric preform pushed into the holes and/or recesses, and a rigidized preform with surface protrusions is formed. The tooling is removed, and the rigidized preform is densified, thereby forming a CMC component including raised surface features.

IPC Classes  ?

• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 35/628 - Coating the powders
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like

Abstract

A method of processing a ceramic matrix composite (CMC) component includes extracting silicon from a surface region of the CMC component such that free silicon is present in the surface region at a reduced amount of about 5 vol. % or less. The extraction comprises contacting the surface region with a wicking medium comprising an element reactive with silicon. The extraction is carried out at an elevated temperature prior to assembling the CMC component with a metal component.

IPC Classes  ?

• C04B 37/02 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/53 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone involving the removal of part of the materials of the treated article
• C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/628 - Coating the powders
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• B28B 1/52 - Producing shaped articles from the material specially adapted for producing articles from mixtures containing fibres
• F01D 5/14 - Form or construction
• B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
• B28B 3/02 - Producing shaped articles from the material by using pressesPresses specially adapted therefor wherein a ram exerts pressure on the material in a moulding spaceRam heads of special form
• B28B 7/16 - Moulds for making shaped articles with cavities or holes open to the surface
• B28B 3/08 - Producing shaped articles from the material by using pressesPresses specially adapted therefor wherein a ram exerts pressure on the material in a moulding spaceRam heads of special form with two or more rams per mould

Abstract

A method of processing a CMC component includes applying a surface formulation comprising a resin and/or a preceramic polymer to a fiber preform. The surface formulation is cured to form a surface coating, which is then pyrolyzed to convert the resin to carbon and/or the preceramic polymer to silicon carbide. After pyrolysis, the fiber preform is infiltrated with a melt comprising silicon to form a CMC component. During melt infiltration, the carbon reacts with the silicon to form silicon carbide, and the silicon carbide prevents unreacted silicon from accessing a surface region of the CMC component. Thus, after melt infiltration, a concentration of free silicon in the surface region is a low amount of about 5 vol. % or less. Upon assembling the CMC component with a metal component, diffusion between the components is inhibited or prevented by the low amount of free silicon in the surface region.

IPC Classes  ?

• C04B 35/83 - Carbon fibres in a carbon matrix
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 35/56 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides
• F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A method of processing a CMC component includes preparing a fiber preform having a predetermined shape, and positioning the fiber preform with tooling having holes facing one or more surfaces of the fiber preform. After the positioning, a clamping pressure is applied to the tooling to force portions of the one or more surfaces of the fiber preform into the holes, thereby forming protruded regions of the fiber preform. During the application of the clamping pressure, the fiber preform is exposed to gaseous reagents at an elevated temperature, and a matrix material is deposited on the fiber preform to form a rigidized preform including surface protrusions. After removing the tooling, the rigidized preform is infiltrated with a melt for densification, and a CMC component having surface bumps is formed. When the CMC component is assembled with a metal component, the surface bumps may reduce diffusion at high temperatures.

IPC Classes  ?

• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/628 - Coating the powders
• C04B 41/87 - Ceramics
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 37/02 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles

Abstract

An example technique includes extruding, by a tow deposition device, on a tow-by-tow basis, respective impregnated tows of a plurality of respective impregnated tows to form a layer of material on a major surface of a substrate. Each respective impregnated tow includes at least one ceramic fiber and a curable resin coating the at least one ceramic fiber. The example technique includes curing the curable resin to form a cured composite component. An example system includes a tow deposition device, an energy source, and a computing device. The computing device is configured to control the tow deposition device to extrude, on a tow-by-tow basis, respective impregnated tows of a plurality of respective impregnated tows to form a layer of material, and is configured to control the energy source to cure the curable resin to form a cured composite component.

IPC Classes  ?

• B28B 1/00 - Producing shaped articles from the material
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
• B33Y 30/00 - Apparatus for additive manufacturingDetails thereof or accessories therefor
• B28B 17/00 - Details of, or accessories for, apparatus for shaping the materialAuxiliary measures taken in connection with such shaping

Abstract

A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits

Abstract

The disclosure describes techniques for forming a surface layer of an article including a CMC using a cast. In some examples, the surface layer includes three-dimensional surface features, which may increase adhesion between the CMC and a coating on the CMC. In some examples, the surface layer may include excess material, with or without three-dimensional surface features, which is on the CMC. The excess material may be machined to remove some of the excess material and facilitate conforming the article to dimensional tolerances, e.g., for fitting the article to another component. The excess material may reduce a likelihood that the CMC (e.g., reinforcement material in the CMC) is damaged by the machining.

IPC Classes  ?

• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C04B 41/52 - Multiple coating or impregnating
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/81 - Coating or impregnating
• C04B 41/85 - Coating or impregnating with inorganic materials
• B33Y 10/00 - Processes of additive manufacturing

Abstract

A blade for a gas turbine engine, and methods of manufacture of such a blade having a continuous density gradient so that the portion of the blade nearest the rotator shaft is of a higher density than the portion of the blade furthest from the rotator shaft.

IPC Classes  ?

• F01D 5/14 - Form or construction
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A method of controllably coating a fiber preform has been developed. The method includes infiltrating a fiber preform with a first solvent to form a solvent-filled preform. After the infiltration, a slurry is applied to one or more outer surfaces of the solvent-filled preform to form a slurry coating thereon. The slurry coating comprises particulate solids dispersed in a second solvent having a vapor pressure higher than that of the first solvent. The slurry coating and the solvent-filled preform are dried. During drying, the second solvent evaporates from the slurry coating before the first solvent evaporates from the solvent-filled preform. The slurry coating dries to form a porous surface coating comprising the particulate solids on the one or more outer surfaces of the solvent-filled preform. The drying of the solvent-filled preform continues after formation of the porous surface coating to remove the first solvent.

IPC Classes  ?

• C04B 35/571 - Fine ceramics obtained from polymer precursors
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 35/58 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides
• C04B 35/10 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on aluminium oxide
• C04B 35/18 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in aluminium oxide
• C04B 35/563 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on boron carbide
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/87 - Ceramics
• C04B 41/50 - Coating or impregnating with inorganic materials
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

Abstract

A method of making a fiber preform for ceramic matrix composite (CMC) fabrication that utilizes a fugitive binder and a machining step is described. The method includes, according to one embodiment, laying up a plurality of plies to form a stack, where each ply comprises an arrangement of fibers. The stack is infiltrated with a polymer at an elevated temperature to form an infiltrated stack that is cooled to form a rigid preform. The rigid fiber preform is machined to have a predetermined shape, such that a machined fiber preform is formed. A composite assembly including the machined fiber preform is formed and then the composite assembly is heated at a sufficient temperature to pyrolyze the polymer. Thus, a porous preform of a predetermined geometry is formed for further processing into a CMC.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/634 - Polymers
• C04B 35/638 - Removal thereof
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/628 - Coating the powders

Abstract

An apparatus for coating specimens includes a reaction chamber and a plurality of reaction modules in the reaction chamber for containing specimens to be coated, where each reaction module includes a module inlet and a module outlet. A plurality of conduits are configured to be in fluid communication with at least one gas source external to the reaction chamber, and each of the conduits terminates in one of the reaction modules for delivery of gaseous reagents to the specimens to be coated. The module outlets are in fluid communication with the reaction chamber for expulsion of gaseous reaction products from the reaction modules.

IPC Classes  ?

• C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
• C04B 41/85 - Coating or impregnating with inorganic materials
• C04B 41/87 - Ceramics
• C04B 41/45 - Coating or impregnating
• C23C 16/32 - Carbides
• C23C 16/34 - Nitrides
• C23C 16/26 - Deposition of carbon only

Abstract

A multi-piece disk for use in a turbine of a gas turbine engine. The multi-piece disk includes a fore disk segment and an aft disk segment coupled with the fore disk segment for movement with the fore disk segment. The fore disk segment and the aft disk segment are formed to define slots that extend through the disk segments and are configured to receive turbine blades therein.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. The blades each fit within slots formed in the rotor disk to couple the blades to the rotor disk. Platform segments are arranged about each of the blades.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/22 - Blade-to-blade connections, e.g. by shrouding
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.

IPC Classes  ?

• F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotorsBlade roots
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/14 - Form or construction

Abstract

A system includes a load actuator, a strain measurement device, and a computing device. The computing device is configured to receive an unconditioned displacement signal from the strain measurement device. The unconditioned displacement signal represents displacement of a specimen under load from the load actuator. The computing device is further configured to split the unconditioned displacement signal into a measurement signal and a control signal. The computing device is further configured to filter the control signal to generate a filtered control signal and control the load actuator based on the filtered control signal. The computing device is further configured to determine a strain on the specimen based on the measurement signal.

IPC Classes  ?

• G01N 3/00 - Investigating strength properties of solid materials by application of mechanical stress
• G01N 3/08 - Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
• G01N 3/02 - Investigating strength properties of solid materials by application of mechanical stress Details

Abstract

Turbine blades for use in gas turbine engines are disclosed herein. Each blade includes an airfoil and a protective crown. The airfoil includes ceramic matrix composite materials. The protective crown includes ceramic-containing materials and is mounted to a radially-outer end portion of the airfoil.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
• F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
• F01D 5/22 - Blade-to-blade connections, e.g. by shrouding

Abstract

A method of forming a ceramic matrix composite (CMC) component having an engineered surface includes applying a surface slurry comprising first particulate solids in a liquid carrier to an outer surface of a ceramic fiber preform. The surface slurry is dried to remove the liquid carrier, and thus a surface slurry layer comprising the first particulate solids is formed on the outer surface. The surface slurry layer is polished to a predetermined thickness and/or surface finish. After polishing, a ceramic tape comprising second particulate solids is applied to the surface slurry layer, and pressure is applied to attach the ceramic tape to the surface slurry layer and to induce consolidation of the ceramic tape and the surface slurry layer. Thus, a multilayer surface region comprising the surface slurry layer and a ceramic tape layer is formed on the ceramic fiber preform. The ceramic fiber preform and the multilayer surface region are infiltrated with a molten material, and, upon cooling, a CMC component having an engineered surface is formed.

IPC Classes  ?

• B32B 18/00 - Layered products essentially comprising ceramics, e.g. refractory products
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/628 - Coating the powders
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like

Abstract

A system and method for forming a porous ceramic preform is provided. The method may include forming a stacked powder structure including a binder layer and a powder layer on the binder layer. The binder layer may be formed by depositing a binder with a spray nozzle on a substrate. The powder layer may be formed by depositing a powder on the binder layer. The porous ceramic preform may be formed by heating the stacked powder structure to pyrolyze the binder. The porous ceramic preform is configured to be infiltrated by a molten material. The substrate may comprise a ceramic fiber preform. After melt infiltration of the porous ceramic preform and the ceramic fiber preform, a densified ceramic feature having a predetermined geometry may be formed on a ceramic matrix composite (CMC) component.

IPC Classes  ?

• B28B 1/00 - Producing shaped articles from the material
• B33Y 10/00 - Processes of additive manufacturing
• B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
• B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
• C04B 35/622 - Forming processesProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products
• C04B 35/628 - Coating the powders
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/571 - Fine ceramics obtained from polymer precursors
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 35/58 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides
• C04B 35/591 - Fine ceramics obtained by reaction sintering
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like

Abstract

A method including infiltrating a porous fiber preform with a slurry including a carrier fluid and a first plurality of solid particles wherein the first plurality of solid particles includes at least a first ceramic material, drying the slurry to form a greenbody preform, machining the greenbody preform to a target dimension, depositing a protective layer precursor including a second plurality of solid particles on the machined greenbody preform wherein the second plurality of solid particles includes at least a second ceramic material, and infiltrating the machined greenbody preform with a molten infiltrant to form a composite article including an integral protective layer.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/628 - Coating the powders
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/573 - Fine ceramics obtained by reaction sintering

Abstract

A method of making a fiber preform for ceramic matrix composite (CMC) fabrication comprises laminating an arrangement of fibers between polymer sheets comprising an organic polymer, which may function as a fugitive binder during fabrication, to form a flexible prepreg sheet. A plurality of the flexible prepreg sheets are laid up in a predetermined geometry to form a stack, and the stack is heated to soften the organic polymer and bond together the flexible prepreg sheets into a bonded prepreg structure. Upon cooling of the bonded prepreg structure, a rigid preform is formed. The rigid preform is heated at a sufficient temperature to pyrolyze the organic polymer. Thus, a porous preform that may undergo further processing into a CMC is formed.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/634 - Polymers
• C04B 35/638 - Removal thereof
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating
• B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
• B29C 48/00 - Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired formApparatus therefor
• B29C 48/08 - Flat, e.g. panels flexible, e.g. films
• B29B 11/00 - Making preforms
• B32B 37/15 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
• B32B 38/00 - Ancillary operations in connection with laminating processes
• C08J 5/12 - Bonding of a preformed macromolecular material to the same or other solid material such as metal, glass, leather, e.g. using adhesives
• B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
• B32B 9/00 - Layered products essentially comprising a particular substance not covered by groups
• C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
• B32B 37/20 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of continuous webs only

Abstract

A method of making a ceramic fiber tow and the system regarding the same may be included. The method may include commingling a plurality of ceramic fibers with a fugitive fiber to form a single ceramic fiber tow. The fugitive fiber may be positioned between at least two ceramic fibers included in the single ceramic fiber tow. The method may further include forming a porous ceramic preform including at least the single ceramic fiber tow. The method may further include removing the fugitive fiber from the ceramic fiber tow leaving a space between at least two ceramic fibers of the single ceramic fiber tow. The method may further include replacing the spaces between ceramic fibers included in the ceramic fiber tows with a ceramic matrix.

IPC Classes  ?

• C04B 35/638 - Removal thereof
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• D02G 3/44 - Yarns or threads characterised by the purpose for which they are designed
• D02J 13/00 - Heating or cooling the yarn, thread, cord, rope, or the like, not specific to any one of the processes provided for in this subclass
• D02J 1/08 - Interlacing constituent filaments without breakage thereof, e.g. by use of turbulent air streams
• C04B 35/622 - Forming processesProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products
• C04B 35/628 - Coating the powders
• D02G 3/04 - Blended or other yarns or threads containing components made from different materials
• B29C 70/18 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length in the form of a mat, e.g. sheet moulding compound [SMC]
• D02J 1/18 - Separating or spreading
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
• B29C 70/36 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and impregnating by casting, e.g. vacuum casting

Abstract

A system may include a reactor vessel comprising an outer wall, a heat source thermally coupled to the reactor vessel, at least one reactor inlet in the outer wall, and at least one reactor outlet. The reactor vessel may be configured to house a porous preform in a radially central core region. The at least one reactor inlet may be configured to introduce a precursor gas to the reactor vessel to produce swirling flow of the precursor gas around the radially central core region of the reactor vessel. The at least one reactor outlet may be configured to remove exhaust gas from the reactor vessel and assist in maintaining a dynamic pressure of the reactor vessel greater than a pressure in the porous preform.

IPC Classes  ?

• C23C 16/04 - Coating on selected surface areas, e.g. using masks
• C23C 16/24 - Deposition of silicon only
• C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
• C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C23C 16/44 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating
• C23C 16/46 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for heating the substrate
• C23C 16/52 - Controlling or regulating the coating process

Abstract

A method of forming a composite article may include impregnating an inorganic fiber porous preform with a first slurry composition. The slurry composition includes particles, a solvent, and a pre-gellant material. Gelling of the pre-gellant material in the slurry composition is initiated to substantially immobilize the particles and yield a gelled article. The method also includes impregnating the gelled article with a second solution that includes a high char-yielding component, and pyrolyzing the high char-yielding component to yield carbon and form a green composite article. The green composite article is then infiltrated with a molten metal or alloy infiltrant to form the composite article. The molten infiltrant reacts with carbon, and the final composite article may include less residual metal or alloy than a composite article formed without using the second solution.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 35/628 - Coating the powders
• C04B 35/624 - Sol-gel processing
• C04B 35/64 - Burning or sintering processes
• C04B 35/65 - Reaction sintering of free metal- or free silicon-containing compositions
• C23C 2/04 - Hot-dipping or immersion processes for applying the coating material in the molten state without affecting the shapeApparatus therefor characterised by the coating material

Abstract

A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
• C23C 16/32 - Carbides
• C23C 16/04 - Coating on selected surface areas, e.g. using masks

Abstract

An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

A method of forming an impurity barrier layer on a CMC substrate may include introducing, to a heated plume of a thermal spray gun, a composite feedstock that includes a first coating material including a plurality of first particles; and a second coating material that may be different from the first coating material, where the second coating material at least partially encapsulates at least a portion of respective surfaces of the plurality of first particles; and directing, using the heated plume, at least the first coating material to a surface of a CMC substrate to deposit an impurity barrier layer including at least the first coating material.

IPC Classes  ?

• C23C 4/04 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
• C23C 4/10 - Oxides, borides, carbides, nitrides or silicidesMixtures thereof
• C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
• C04B 41/52 - Multiple coating or impregnating
• C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
• B01J 20/30 - Processes for preparing, regenerating or reactivating

Abstract

A method of forming a moisture-tolerant coating on a silicon carbide fiber includes exposing a silicon carbide fiber to a gaseous N precursor comprising nitrogen at an elevated temperature, thereby introducing nitrogen into a surface region of the silicon carbide fiber, and exposing the silicon carbide fiber to a gaseous B precursor comprising boron at an elevated temperature, thereby introducing boron into the surface region of the silicon carbide fiber. Silicon-doped boron nitride is formed at the surface region of the silicon carbide fiber without exposing the silicon carbide fiber to a gaseous Si precursor comprising Si. Thus, a moisture-tolerant coating comprising the silicon-doped boron nitride is grown in-situ on the silicon carbide fiber.

IPC Classes  ?

• C23C 16/34 - Nitrides
• C04B 35/628 - Coating the powders
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C23C 16/30 - Deposition of compounds, mixtures or solid solutions, e.g. borides, carbides, nitrides
• D06M 11/58 - Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with inorganic substances or complexes thereofSuch treatment combined with mechanical treatment, e.g. mercerising with nitrogen or compounds thereof, e.g. with nitrides
• D06M 11/80 - Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with inorganic substances or complexes thereofSuch treatment combined with mechanical treatment, e.g. mercerising with boron or compounds thereof, e.g. borides
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• D06M 101/16 - Synthetic fibres, other than mineral fibres

Abstract

A method of forming a composite article includes impregnating an inorganic fiber preform with a slurry composition. The slurry composition includes a particulate, a solvent, and a pre-gellant material. Gelling of the pre-gellant material in the slurry composition is initiated to immobilize the particulate and yield a gelled article, and substantially all solvent is removed from the gelled article to form a green composite article. The green composite article is then infiltrated with a molten infiltrant to form the composite article.

IPC Classes  ?

• C04B 41/85 - Coating or impregnating with inorganic materials
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/45 - Coating or impregnating
• C04B 41/87 - Ceramics
• C04B 41/53 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone involving the removal of part of the materials of the treated article
• C04B 41/52 - Multiple coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 35/626 - Preparing or treating the powders individually or as batches
• C04B 35/628 - Coating the powders
• C04B 35/634 - Polymers
• C04B 35/636 - Polysaccharides or derivatives thereof
• C04B 35/622 - Forming processesProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products
• C04B 35/624 - Sol-gel processing
• C04B 35/65 - Reaction sintering of free metal- or free silicon-containing compositions
• C04B 35/657 - Processes involving a melting step for manufacturing refractories

Abstract

A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

A method of slurry infiltration and cleaning to fabricate a ceramic matrix composite (CMC) component with an internal cavity or bore comprises inserting a number of rods into a hollow portion of a porous fiber preform, thereby forming a rod arrangement substantially filling the hollow portion. Each of the rods has a low-friction surface comprising a coefficient of static friction of about 0.1 or less. The porous fiber preform is exposed to a slurry comprising particulate solids in a liquid carrier, and the slurry infiltrates the porous fiber preform. Some fraction of the particulate solids is deposited within interstices of the porous fiber preform to form an impregnated fiber preform, and another fraction of the particulate solids is deposited within the hollow portion as excess slurry. After slurry infiltration, the rods are withdrawn from the hollow portion, and at least some of the excess slurry is removed with the rods.

IPC Classes  ?

• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• B08B 9/04 - Cleaning the internal surfacesRemoval of blockages using cleaning devices introduced into and moved along the pipes
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/00 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products

Abstract

A ceramic matrix composite (CMC) is formed using a three-dimensional (3-D) woven preform by removing the set of sacrificial fibers from the 3-D woven preform and allowing a metal or metal alloy infiltrate the 3-D woven preform. The 3-D woven preform is formed by a method that includes providing a woven layer comprising a first set of ceramic fibers oriented in a first (x) direction woven with a second set of ceramic fibers oriented in a second (y) direction; stacking a plurality of woven layers on top of each other, said woven layers providing a two-dimensional (2-D) preform; weaving a set of sacrificial fibers in a third (z) direction with the 2-D preform, said weaving providing the 3-D woven preform; and shaping the 3-D woven preform into a predetermined shape.

IPC Classes  ?

• C22C 47/08 - Making alloys containing metallic or non-metallic fibres or filaments by contacting the fibres or filaments with molten metal, e.g. by infiltrating the fibres or filaments placed in a mould
• C22C 47/06 - Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element
• B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
• D03D 11/00 - Double or multi-ply fabrics not otherwise provided for
• B32B 1/00 - Layered products having a non-planar shape
• B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
• C04B 35/622 - Forming processesProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products
• C23C 16/04 - Coating on selected surface areas, e.g. using masks
• D03D 25/00 - Woven fabrics not otherwise provided for
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• C04B 41/51 - Metallising
• D03D 15/68 - Scaffolding threads, i.e. threads removed after weaving

Abstract

A ceramic matrix composite (CMC) is formed by infiltrating a metal or alloy into a fiber preform in a reactor or furnace that is separated into multiple discrete temperature zones. The gradual cooling of the CMC is controlled, such that upon solidification, a narrow, planar, solidification front is created which allows the expanding metal or alloy to move into a hotter section of the fiber preform, opposed to the surface of the CMC. A discrete solidification front is established that moves through the ceramic matrix composite (CMC) as the composite cools.

IPC Classes  ?

• C23C 2/00 - Hot-dipping or immersion processes for applying the coating material in the molten state without affecting the shapeApparatus therefor
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 35/64 - Burning or sintering processes

Abstract

Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assemblies include a carrier and a blade track. The blade track extends around blades of a turbine wheel assembly to block gasses passed along a gas path from moving over the blades without causing the blades to rotate during operation of the turbine assembly. The blade track includes a plurality of blade track segments arranged circumferentially adjacent to one another about a central axis to form a ring. A retention ring engages both the carrier and the blade track segments to facilitate coupling and sealing.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

A turbine shroud adapted for use in a gas turbine engine includes an attachment feature and a body. The attachment feature and the body are constructed of ceramic matrix composite materials. In an illustrative embodiment, the ceramic matrix composite materials form a blade track segment.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

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.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 41/52 - Multiple coating or impregnating
• C04B 35/571 - Fine ceramics obtained from polymer precursors
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 35/76 - Fibres, filaments, whiskers, platelets, or the like
• C04B 38/06 - Porous mortars, concrete, artificial stone or ceramic warePreparation thereof by burning-out added substances
• B32B 18/00 - Layered products essentially comprising ceramics, e.g. refractory products

Abstract

An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The assembly also includes a retention assembly for coupling the supported component to the carrier.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

Abstract

A method for fabricating a ceramic matrix composite component having a deltoid region is provided. The method includes providing a porous ceramic preform. The porous ceramic preform includes a layer-to-layer weave of ceramic fibers that forms a modified layer-to-layer woven core and at least one 2-dimensional layer of ceramic fibers that is disposed adjacent to the modified layer-to-layer woven core. The porous ceramic preform is formed into a ceramic matrix composite body having the deltoid region such that the modified layer-to-layer woven core extends through the deltoid region.

IPC Classes  ?

• C04B 41/51 - Metallising
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A method of melt infiltration for producing a ceramic matrix composite comprises applying a non-wetting coating onto one or more outer surfaces of a porous fiber preform. The non-wetting coating comprises a non-wetting material with which molten silicon has a contact angle of at least about 45°. After applying the non-wetting coating, an uncoated portion of the porous fiber preform is immersed into a molten material comprising silicon, and the molten material is infiltrated into the porous fiber preform through the uncoated portion. The non-wetting coating serves as a barrier to inhibit or prevent the molten material from penetrating the one or more outer surfaces. After infiltration of the molten material into the porous fiber preform, the molten material is cooled to form a ceramic matrix composite, and the non-wetting coating is removed.

IPC Classes  ?

• B05D 1/18 - Processes for applying liquids or other fluent materials performed by dipping
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 35/628 - Coating the powders
• B05D 1/02 - Processes for applying liquids or other fluent materials performed by spraying
• B05D 1/28 - Processes for applying liquids or other fluent materials performed by transfer from the surfaces of elements carrying the liquid or other fluent material, e.g. brushes, pads, rollers
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• C04B 35/573 - Fine ceramics obtained by reaction sintering

Abstract

A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• C04B 35/628 - Coating the powders
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/52 - Multiple coating or impregnating
• C04B 35/573 - Fine ceramics obtained by reaction sintering
• C04B 41/50 - Coating or impregnating with inorganic materials

Abstract

A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine. The turbine vane is made from ceramic matrix composite materials with three-dimensionally woven or braided reinforcing tows and includes an inner band, an outer band, and an airfoil that extends between the inner band and the outer band.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades