United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Pratt-whitney Canada Corp

Other

Otis Elevator Company

Pratt & Whitney Rocketdyne, Inc.

David C Jarmon

Wayde R Schmidt

Xia Tang

Paul Sheedy

Jun Shi

Karl M Prewo

William K Tredway

Shaoluo L Butler

Lev Alexander Prociw

James Thompson Beals

Tania Bhatia Kashyap

John G Smeggil

Tania Bhatia

Robert J Miller

David J Bombara

Owen B Donahue, Jr

Steven Wayne Burd

Stephen Karl Kramer

Jean Yamanis

Harry E Eaton

Mark Steven Thompson

Pedro S Baranda

Michael K Sahm

Rhonda R Willigan

Aleksandar Kojovic

Paul Attridge

Richard Sterling Tuthill

Kevin E Green

Roy N Guile

Peter Gerard Smith

Harry Edwin Eaton, Jr

Otis Y Chen

Glenn Michael Allen

Stuart S Ochs

Jeffrey D Melman

Harold M Craig

Eric Minford

Michael R Kracum

R Wesley Jackson

Bradley C Johnson

Steven A Lozyniak

Lee A Hoffman

Lisa A Prill

Aleksander Kojovic

Mark E Palusis

Jason Lawrence

Mark A Sillence

Nikolaos Napoli

Bruce Bond

Christopher Dale Jones

Virginia H Faustino

Steve Lozyniak

Michael T Weber

Xiaolan Hu

Christopher L Kogstrom

Jeffery C Moree

Richard S Tuthill

Lev A Prociw

A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a healing silica matrix and at least one oxygen scavenger forming a metal silicide network dispersed within the healing silica matrix; and a top coat layer disposed upon the oxidation resistant bond coat layer, whereby the oxidation resistant bond coat layer is operable to seal a crack in the top coat layer.

Oxidation resistant bond coat layers, processes for coating articles, and their coated articles

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

Integral ceramic matrix composite fastener with polymer rigidization

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Integral ceramic matrix composite fastener with non-polymer rigidization

A method of making an ceramic article according to an exemplary embodiment of this disclosure, among other possible things includes arranging fiber plies into a preform, inserting one or more sacrificial springs to the preform, infiltrating the preform with a matrix material to form an article, and thermally degrading the one or more sacrificial springs to form cooling holes. A ceramic article and a gas turbine engine component are also disclosed.

Article with cooling holes and method of forming the same

An apparatus for making a composite article includes a monofilament feed track adapted to carry a spaced array of ceramic monofilament strands, a fiber yarn feed track adapted to carry a spaced array of fiber yarn tows impregnated with a plurality of glass particulates, a mandrel, and a heater assembly. The mandrel is adapted to wind together individual glass-impregnated fiber yarn strands and individual ceramic monofilament strands to form a dual-fiber weave. The heater assembly is adapted to heat at least the glass particulates such that pressure from the wound array of ceramic monofilaments is sufficient to consolidate the glass particulates and the dual-fiber weave into a dual-fiber ceramic matrix composite (CMC).

Filament winding apparatus and method for ceramic matrix composites

Methods for fabricating a ceramic matrix composite are disclosed. A fiber preform may be placed in a mold. An aqueous solution may be added to the fiber preform. The aqueous solution may include water, carbon nanotubes, and a binder. The preform may be frozen. Freezing the preform may cause the water to expand and separate fibers in the fiber preform. The carbon nanotubes may bond to the fibers. The preform may be freeze dried to remove the water. The preform may then be processed according to standard CMC process.

Systems and methods for ceramic matrix composites

One exemplary embodiment of this disclosure relates to a transfer molding assembly including a chamber, a die within the chamber, a first gas control device configured to provide a first gas into the chamber, and a second gas control device configured to provide a second gas into the die.

Assembly and method for transfer molding

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

A disclosed method includes serially moving a plurality of dies through a series of interconnected chambers that are selectively sealable from each other. Through the series of interconnected chambers, each of the dies is introduced into a controlled gas environment, each of the dies is introduced into a controlled temperature environment, a process-environment-sensitive material is pressurized in each of the dies, and each of the dies is cooled. A disclosed apparatus includes a series of interconnected chambers that are selectively sealable from each other. A first one of the chambers is configured to establish a controlled gas environment therein, a second one of the chambers is configured to establish a controlled temperature environment therein, a third one of the chambers is configured to pressurize a process-environment-sensitive material and a fourth one of the chambers is configured to cool the process-environment-sensitive material.

Method and apparatus for processing process-environment-sensitive material

An article comprising a substrate and at least one coating layer disposed on the substrate. The coating layer includes a silicate glass matrix, an oxygen scavenger phase dispersed through the silicate glass matrix, and at least one metal in metallic form.

Article having coating with glass, oxygen scavenger, and metal

Growing community of inventors

Kensington, CT, United States of America

David C Jarmon