General Electric Company

Larry Steven Rosenzweig

Shankar Sivaramakrishnan

Bernard Patrick Bewlay

James Anthony Ruud

Ambarish Jayant Kulkarni

Hrishikesh Keshavan

Mehmet Muhittin Dede

Byron Andrew Pritchard

Krzysztof Jacek Lesnicki

Jay Morgan

Neelesh Nandkumar Sarawate

Julin Wan

Venkat Subramaniam Venkataramani

Curtis Alan Johnson

Krishan Lal Luthra

Mohan Manoharan

Changjie Sun

Ananda Barua

Reza Sarrafi-Nour

Sathyanarayanan Raghavan

Brian Harvey Pilsner

Alok Mani Srivastava

Wayne Charles Hasz

Glen Harold Kirby

Don Mark Lipkin

Byron Andrew Pritchard, Jr

Peter Joel Meschter

Hongyu Wang

Mark Markovitz

Jinjie Shi

Mohandas Nayak

Joshua Lee Margolies

Digamber Gurudas Porob

Stephen Francis Bancheri

Gopi Chandran Ramachandran

Margeaux Wallace

Scott Sheridan Smith

Edip Sevincer

Kenneth Martin Lewis

Michael Patrick Manning

Anthony Christopher Marin

Robert Timothy Lembke

Kristen Hall Brosnan

Shahana Chatterjee

Julie Marie Chapman

Paul Matthew Thomas

Luc Stèphane Leblanc

Methods for preparing an environmental barrier coating and the resulting coating are provided. The methods and products include the incorporation of a continuous ceramic inner layer and a segmented ceramic outer layer on a CMC component. The segmented ceramic outer layer may be formed by thermal spray techniques. The coating is more stable at higher temperatures and provides for a longer lifetime of the coated component.

Segmented environmental barrier coating systems and methods of forming the same

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

An atomizing spray device includes a housing having plural inlets and one or more outlets fluidly coupled with each other by an interior chamber. The inlets include a first inlet shaped to receive a first fluid and a second inlet shaped to receive a slurry of ceramic particles and a second fluid. The interior chamber in the housing is shaped to mix the first fluid received via the first inlet with the slurry received via the second inlet inside the housing to form a mixture in a location between the inlets and the one or more outlets. The interior chamber in the housing also is shaped to direct the mixture formed inside the housing as droplets outside of the housing via the one or more outlets such that, based on a discharged amount of the first fluid in the droplets, the first fluid promotes evaporation of the second fluid as the droplets traverse from the housing toward a surface of a component.

Coating system and method

A control system includes one or more processors configured to determine when to extend a life span of an engine by applying an additional restorative coating to the engine based on one or more monitored parameters of the engine. The monitored parameters include a condition of a previously applied restorative coating. The one or more processors are configured to determine the condition of the previously applied restorative coating based on an optical response of the previously applied restorative coating. The one or more processors also are configured to direct application of the additional restorative coating based on the one or more monitored parameters of the engine.

Control system and method

A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.

Turbine systems with sealing components

Systems and methods that provide or restore a coating to a component are provided. The systems and methods utilized an atomizing spray device. A gas and a slurry that comprises fluid and ceramic particles are supplied to the atomizing spray device. The slurry and gas are discharged from the spray device to form two-phase droplets. The fluid within the droplets evaporates to prevent the fluid from becoming part of the coating as the droplets traverse through the air and prior to impacting the surface of the component.

Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.

Abradable coating composition for compressor blade and methods for forming the same

Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include a ceramic material disposed along the compressor blade tip and may be used with a bare compressor casing. The ceramic coating is harder than the bare compressor casing and can reduce the rub ratio thereby increasing the lifetime of the compressor blades. Methods are also provided for applying the coating system onto a compressor blade.

Ceramic coating compositions for compressor blade and methods for forming the same

A control system having one or more controllers configured to determine a maintenance date of an engine based on monitored parameters of the engine of an aircraft. The one or more controllers also are configured to, determine an amount of coating sprayed on the engine on the determined maintenance date based on the monitored parameters and determined maintenance date. The one or more controllers also are configured to adjust the maintenance date based on needs of an aircraft fleet and regularly scheduled maintenance of the engine.

A coated component, along with methods of its formation, restoration, and use, is provided. The coated component may include a substrate defining a surface; a thermal barrier coating on the surface of the substrate; a layer of environmental contaminant compositions (e.g., CMAS) on the thermal barrier coating; and a chemical barrier coating on the layer of environmental contaminant compositions.

CMAS barrier coating for a gas turbine engine having a reactive material that reacts with a layer of environmental contaminant compositions and method of applying the same

Systems and methods that provide or restore a coating to a component are provided. The systems and methods utilized an atomizing spray device. A slurry that comprises a fluid and ceramic particles, and a gas are supplied to the atomizing spray device. The slurry and gas are discharged from the spray device to form two-phase droplets. The fluid within the droplets evaporates to prevent the fluid from becoming part of the coating as the droplets traverse through the air and prior to impacting the surface of the component.

An article having a damage-tolerant thermal barrier coating includes a plurality of coating layers disposed over a substrate. The plurality of coatings comprises an inner layer and an outer layer. The outer layer is more resistant to infiltration by nominal CMAS relative to 8 weight percent yttria-stabilized zirconia at a temperature of 1300 degrees Celsius. The inner layer has, in a temperature range from about 1000 degrees Celsius to about 1200 degrees Celsius, a thermal resistance in a range from about 9&#xd7;10degree Kelvin per watt to about 23&#xd7;10degree Kelvin per watt.

Articles having damage-tolerant thermal barrier coating

The present application provides Calcia-Magnesia-Alumina-Silica (CMAS) (or molten silicate) resistant thermal barrier coatings (TBC). The coatings include elongate growth domains of non-equiaxed, randomly arranged overlapping grains or splats. The elongate growth domains include overlapping individual, randomly distributed splats of tough and soft phases. In some embodiments, the elongate growth domains are formed via air plasma spray. In some embodiments, the tough phases are at least partially stabilized zirconia and/or hafnia compositions, and the soft phases are CMAS (or molten silicate) reactive or resistant compositions. Within each elongate growth domain, the mixture of the tough and soft phases act together to limit penetration of CMAS and also provide sufficient domain toughness to minimize cracking forces produced during crystallization of infiltrated CMAS. The soft phases may react with the CMAS and increase its melting point, increase its viscosity, and reduce the destabilization of the tough phases.

CMAS resistant thermal barrier coatings

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Clifton Park, NY, United States of America

Larry Steven Rosenzweig