Honeywell International Inc.

Bahram Jadidian

Mehrad Mehr

James Piascik

Reza Oboodi

Eric Passman

John Downs

Mahdi Mohajeri

Donald Martin Olson

Terence Whalen

Harry Lester Kington

Paul Chipko

Richard George Rateick, Jr

Kevin Blinn

Neil Murdie

Jimmy Wiggins

Robert Alan Dietrich

Amer Aizaz

Gangmin Cao

Jingkang Lv

Yongbae Jung

Christopher Evans

Andre Robinson

Tom McHugh

Robert Mantz

An apparatus includes a first component comprising a carbon composite substrate. A high temperature coating is disposed on the surface of the carbon composite substrate. The high temperature coating includes a bond layer of a metal carbide on the surface of the substrate. The apparatus includes a second component, and braze material joining the surface of the first component to the second component. In some examples, a brake assembly may include a rotor having a surface configured to interface with another component of the brake assembly. The brake assembly includes an insert joined to the surface of the rotor without a mechanical fastener, and the insert defines a tough mechanical contact surface configured to protect the rotor.

High temperature brazing of metals and ceramics to carbon substrates

Components of gas turbine engines, aircraft comprising the components, and methods of producing the components are provided. The component includes a surface, and a set of tiles secured to the surface at interfaces between the set of tiles and the surface and between each of the set of tiles. The set of tiles conform to the surface and in combination define a coating system on the surface that includes an environmental barrier coating and/or a thermal barrier coating.

Components having coating systems defined by tiles secured thereto, methods of producing the components, and aircraft comprising the components

Components having coating systems that include mud cracks, methods for forming the coating systems, and vehicles including the components are provided. The components include a substrate having silicon nitride and a coating system on a surface of the substrate. The coating system includes a first layer of a first coating material on the substrate, wherein the first coating material includes a rare earth silicate and has a first thickness measured in a direction perpendicular to the surface of the substrate, and a second layer of a second coating material on the first layer, wherein the second coating material includes a rare earth silicate and has a second thickness that is greater than the first thickness. The second layer includes mud cracks that extend from an exterior surface thereof toward the substrate, and the mud cracks have widths in a range of about 50 to 200 micrometers.

Components having coating systems comprising mud cracks and methods for forming the coating systems

A method for forming a high temperature coating includes applying carbon powder to a surface of a carbon/carbon (C/C) composite substrate to force the carbon powder into one or more surface voids of the surface of the C/C composite substrate. The carbon powder has a substantially same composition and morphology as a surface portion of the C/C composite substrate. The method includes applying a metal slurry to the surface of the C/C composite substrate following the application of the carbon powder and reacting a metal of the metal slurry with carbon of the carbon powder and carbon of the surface portion of the C/C composite substrate to form a metal-rich antioxidant layer of a metal carbide on the C/C composite substrate.

High temperature metal carbide coatings

Methods and systems are provided for filling cracks in an environmental barrier coating and/or a thermal barrier coating (EBC/TBC). The method comprises locating a component within an enclosure of an apparatus, the component including a substrate having the EBC/TBC thereon, wherein the EBC/TBC includes cracks extending from an exterior surface of the EBC/TBC toward the substrate, reducing pressure within the enclosure to a first pressure that is less than atmospheric pressure, applying a filler slurry to the exterior surface to cover the cracks while the EBC/TBC is exposed to the first pressure, increasing the enclosure to a second pressure that is greater than the first pressure, wherein the second pressure is sufficient to cause the filler slurry on the EBC/TBC to infiltrate into and fill the cracks, and sintering the filler slurry sufficient to cure the filler slurry within the cracks.

Methods and systems for filling cracks in environmental barrier coatings and thermal barrier coatings and components formed thereby

A method for forming a high temperature coating includes forming a pre-sintered ceramic coating on a ceramic composite substrate. The pre-sintered ceramic coating includes a plurality of ceramic particles. The method further includes sintering at least a portion of the pre-sintered ceramic coating by heating the portion of the pre-sintered ceramic coating to a sintering temperature of the plurality of ceramic particles using joule heating. The sintering temperature is greater than about 1000 degrees Celsius (° C.).

Contact joule heating for sintering high temperature coatings

An article including carbon-carbon composite substrate may be treated with an antioxidant coating prior to use in an oxidizing environment. The antioxidant coating may be configured to reduce oxidation at an external surface of the C—C composition and reduce ingress of oxidants into pores or other open passages defined by the C—C composite substrate to avoid internal oxidation. An example article includes a C—C composite substrate, a bond coat, and an antioxidant coating. The C—C composite substrate defines a friction surface and a non-friction surface. The bond coat is disposed on the non-friction surface. The antioxidant coating may be disposed on at least a portion of the bond coat. The antioxidant coating may include ytterbium disilicate and a sintering aid.

Carbon-carbon composite including antioxidant coating

A method of making an electromagnetic coil for use in a high-temperature electromagnetic machine includes pre-coating magnet wire with a high-temperature insulation precursor to produce pre-coated magnet wire, winding, while applying in-situ a glass-ceramic slurry, the pre-coated magnet wire into a predetermined coil shape to produce a wet-wound green coil, and thermally processing the wet-wound green coil to produce a processed coil. In some instances, a second layer of a high-temperature insulation may be applied to the processed coil to produce a further insulated processed coil, and then thermally processing the further insulated processed coil to produce a further processed electromagnetic coil.

Method of assembling a high-temperature electromagnetic machine

A multilayer protective coating system includes a turbine engine component substrate formed of a ceramic matrix composite material, an environmental barrier coating layer including a rare earth disilicate material deposited directly on the substrate, and a plurality of pairs of alternating layers of the rare earth disilicate material and a rare earth monosilicate material deposited and sintered directly on the environmental barrier coating layer. Each layer of the plurality of pairs of alternating layers is relative less thick as compared with the environmental barrier coating layer.

Multilayer protective coating systems for gas turbine engine applications and methods for fabricating the same

In some examples, a method of making a filter includes heating a metal substrate to precipitate a first phase on a surface of the metal substrate from a metal alloy, the metal substrate defining a plurality of apertures configured to allow a gas to pass through the apertures. The metal substrate is the metal alloy including a first metal and a second metal. The method further includes growing a plurality of carbon nanotubes (CNTs) on the surface of the first metal of the first phase, and the CNTs are configured to capture at least one particle.

Filter media and system using the same

An article for a high temperature environment includes a first ceramic composite substrate, a second ceramic composite substrate, and a high temperature interface between a first surface of the first ceramic composite substrate and a second surface of the second ceramic composite substrate. The high temperature interface includes at least one high temperature interface layer that includes a ceramic matrix and a plurality of fibers distributed through the ceramic matrix.

High temperature interfaces for ceramic composites

A protective coating system includes a turbine engine component substrate formed of a ceramic matrix composite material, an environmental barrier coating layer including a rare earth disilicate material formed directly on the substrate, and a thermal barrier coating layer including a porous rare earth monosilicate material having a metal silicate material infiltrated within at least a portion of the pores formed directly on the environmental barrier coating layer.

Protective coating systems for gas turbine engine applications and methods for fabricating the same

A method of pressure sintering an environmental barrier coating on a surface of a ceramic substrate to form an article is provided. The method includes the steps of etching the surface of the ceramic substrate to texture the surface, disposing an environmental barrier coating on the etched surface of the ceramic substrate. The environmental barrier coating includes a rare earth silicate, and pressure sintering the environmental barrier coating on the etched surface of the ceramic substrate in an inert or nitrogen atmosphere such that at least a portion of the environmental barrier coating is disposed in the texture of the surface of the ceramic substrate thereby forming the article.

Method of pressure sintering an environmental barrier coating on a surface of a ceramic substrate

A method of applying a protective coating to a substrate includes the steps of: providing a turbine engine component substrate formed of a ceramic matrix composite material, forming an environmental barrier coating layer including a rare earth disilicate material directly on the substrate, treating an outer surface of the environmental barrier coating layer to form a thermal barrier coating layer including a porous rare earth monociliate material directly on the environmental barrier coating layer. The step of treating the outer surface is performed using a thermal process consisting of the application of heat or a chemical-thermal process consisting of the application of heat and a chemical. The method further includes infiltrating at least a portion of the pores with a metal solution or suspension.

Methods for fabricating protective coating systems for gas turbine engine applications are provided. An exemplary method of applying a protective coating to a substrate includes the steps of providing a substrate formed of a ceramic matrix composite material, forming a first coating layer directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and forming a second coating layer directly on to the first coating layer and comprising a thermal barrier material. The method optionally includes forming a third coating layer partially directly on to the second coating layer and partially within at least some of the plurality of pores of the second coating layer.

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Watchung, NJ, United States of America

Bahram Jadidian