General Electric Company

Other

Krishan Lal Luthra

Peter Joel Meschter

Gregory Scot Corman

Hongyu Wang

Reza Sarrafi-Nour

Milivoj Konstantin Brun

William Patrick Allen

James L Smialek

Kang Neung Lee

Harry Edwin Eaton, Jr

Nathan S Jacobson

Elizabeth J Opila

Curtis Alan Johnson

Julin Wan

Jared Hogg Weaver

Raj N Singh

Badri Narayan Ramamurthi

Narendra Digamber Joshi

Bangalore Aswatha Nagaraj

Irene T Spitsberg

Don Mark Lipkin

Robert A Miller

Larry Steven Rosenzweig

David Joseph Mitchell

Jennifer Su Saak

Ronald Scott Bunker

Glen Harold Kirby

Svante Prochazka

Mohan Manoharan

Venkat Eswarlu Tangirala

Christian Lee Vandervort

Joel Meier Haynes

D Sangeeta

William Paul Minnear

Anthony Mark Thompson

Henry Charles McGuigan

Vidya Ramaswamy

Anteneh Kebbede

Hongbo Cao

Roman Shuba

Narottam P Bansal

Douglas W McKee

Vijay Kumar Srivastava

Geoffrey Mark Eadon

Nathaniel Patrick Brown

Vikas Behrani

Henry S Spacil

Nanottam P Bansal

Don M Lipkin

Gregory Scott Corman

Reza Saraffi-Nour

A coated component may have a consumable coating that protects the component from dust. A coated component may include a silicon containing substrate defining a substrate surface, a barrier coating on the substrate surface, with the barrier coating defining a barrier surface, and a consumable coating on the barrier surface. The consumable coating may include a ceramic oxide that includes a silicate. A component, such as a component of a turbomachine, may be protected from dust by applying a consumable coating on the component.

Consumable coatings and methods of protecting a high temperature component from dust deposits

An article for high temperature service is presented herein. One embodiment is an article including a substrate having a silicon-bearing ceramic matrix composite; and a layer disposed over the substrate, wherein the layer includes silicon and a dopant, the dopant including aluminum. In another embodiment, the article includes a ceramic matrix composite substrate, wherein the composite includes a silicon-bearing ceramic and a dopant, the dopant including aluminum; a bond coat disposed over the substrate, where the bond coat includes elemental silicon, a silicon alloy, a silicide, or combinations including any of the aforementioned; and a coating disposed over the bond coat, the coating including a silicate (such as an aluminosilicate or rare earth silicate), yttria-stabilized zirconia, or a combination including any of the aforementioned.

Article for high temperature service

According to a method set forth herein a plurality of preform plies having first and second preform plies can be associated together to define a preform. The preform can be subject to chemical vapor infiltration (CVI) processing to define a ceramic matrix composite (CMC) structure.

Ceramic matrix composite structures with controlled microstructures fabricated using chemical vapor infiltration (CVI)

Coated components, along with methods of their formation, are provided. The coated component includes a ceramic substrate having a surface; an intermediate layer on the surface of the ceramic substrate; and an environmental barrier coating on the intermediate layer. The intermediate layer includes a carbon-sink material that inhibits accumulation of free carbon from a carbon-containing species within the intermediate layer, the ceramic substrate, or both.

Ceramic composites with an intermediate layer having a carbon sink material for high temperature applications

A coated component, along with methods of its formation and use, is provided. The coated component includes a ceramic matrix composite (CMC) substrate comprising silicon carbide and having a mullite bondcoat on its surface. The mullite bondcoat includes an oxygen getter phase contained within a mullite phase. For example, the mullite bondcoat may include 60% to 98% by volume of the mullite phase. An environmental barrier coating is on the mullite bondcoat.

EBC with mullite bondcoat that includes an oxygen getter phase

An article comprises a substrate comprising a ceramic matrix composite; a first layer disposed over the substrate, the first layer comprising a substantially interconnected silicon source material, and a secondary material; and a second layer disposed over the first layer, the second layer comprising a membrane material in mass transfer communication with the silicon source material.

A ceramic matrix composite article includes a melt infiltration ceramic matrix composite substrate comprising a ceramic fiber reinforcement material in a ceramic matrix material having a free silicon proportion, and a chemical vapor infiltration ceramic matrix composite outer layer comprising a ceramic fiber reinforcement material in a ceramic matrix material having essentially no free silicon proportion disposed on an outer surface of at least a portion of the substrate.

Ceramic matrix composite articles and methods for forming same

A coated component, along with methods of making and using the same, is provided. The coated component includes a ceramic matrix composite (CMC) substrate comprising silicon carbide and having a surface; a mullite/NOSC bondcoat on the surface of the substrate; and an environmental barrier coating on the mullite/NOSC bondcoat. The mullite/NOSC bondcoat comprises a non-oxide silicon ceramic (NOSC) phase contained within a mullite phase, with the mullite/NOSC bondcoat comprising 60% to 95% by volume of the mullite phase, such as 65% to 93% by volume of the mullite phase.

EBC with mullite bondcoat having a non-oxide silicon ceramic

High-temperature machine components, more particularly, articles capable of operating in high-temperature environments, including for example turbines of gas engines, may be formed of a high temperature ceramic matrix composite that includes a ceramic substrate including silicon; an environmental harrier coating system including a silicon containing bond coat; and a diffusion barrier layer of a carbide or a nitride between the substrate of the article and the silicon bond coat of the environmental barrier coating system. The diffusion harrier layer selectively prevents or reduces the diffusion of boron and impurities from the substrate to the bond coat of the environmental barrier coating system.

High temperature tolerant ceramic matrix composites and environmental barrier coatings

The present disclosure relates to ceramic matrix composites made by chemical vapor infiltration, methods of making the ceramic matrix composites, and ceramic matrix composite turbine components for use in a hot gas pathway. A method of fabricating a ceramic matrix composite is provided that can include the steps of: (i) forming a plurality of holes in a ceramic matrix composite preform of desired shape; and (ii) densifying the preform by a chemical vapor infiltration process to form a part or most of the matrix. A ceramic matrix composite is also provided that can be used in hot combustion gases made according to the aforementioned ceramic matrix composite fabrication method described herein.

Ceramic matrix composites made by chemical vapor infiltration and methods of manufacture thereof

Ceramic matrix composite articles include, for example, a plurality of unidirectional arrays of fiber tows in a matrix having a monomodal pore size distribution, and a fiber volume fraction between about 15 percent and about 35 percent. The articles may be formed by, for example, providing a shaped preform comprising a prepreg tape layup of unidirectional arrays of fiber tows, a matrix precursor, and a pore former, curing the shaped preform to pyrolyze the matrix precursor and burnout the pore former so that the shaped preform comprises the unidirectional arrays of fiber tows and a porous matrix having a monomodal pore size distribution, and subjecting the cured shaped preform to chemical vapor infiltration to densify the porous matrix so that the ceramic matrix composite article has a fiber volume fraction between about 15 percent and about 35 percent.

Ceramic matrix composites having monomodal pore size distribution and low fiber volume fraction

A method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a first position. A firing temperature of the gas turbine engine is determined based on the exhaust gas temperature. The firing temperature is compared to a threshold value and a difference value is determined therefrom. If the difference value exceeds a threshold value, the first stage turbine nozzle assembly is adjusted to a second position such that the firing temperature is substantially equal to the threshold value.

Method and system to increase gas turbine engine durability

A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.

Turbine engine assembly and method of assembling the same

A method for forming a ceramic matrix composite article includes forming by melt infiltration a ceramic matrix composite substrate inducing a ceramic fiber reinforcement material in a ceramic matrix material having a free silicon proportion and forming by chemical vapor infiltration a ceramic matrix composite outer layer including a ceramic fiber reinforcement material in a ceramic matrix material having no free silicon proportion disposed on at least a portion of the substrate.

Growing community of inventors

Niskayuna, NY, United States of America

Krishan Lal Luthra