Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

United Technologies Corporation

Rolls-royce High Temperature Composites Inc.

Hamilton Sundstrand Corporation

Pratt-whitney Canada Corp

Sikorsky Aircraft Corporation

Rolls-royce American Technologies, Inc.

Rolls-royce Cornoration

Jun Shi

Ted Joseph Freeman

David John Thomas

Daniel Kent Vetters

Kevin E Green

Li Li

Aaron D Sippel

Shaoluo L Butler

Douglas David Dierksmeier

Jeffrey Allen Walston

Todd Engel

David C Jarmon

Sungbo Shim

Glenn Levasseur

Gajawalli V Srinivasan

Richard Sterling Tuthill

William G Cummings, Iii

Lev Alexander Prociw

Aaron T Nardi

Andrew J Eifert

Peter Broadhead

Tracy A Propheter-Hinckley

Tahany Ibrahim El-Wardany

Ann Bolcavage

Wayde R Schmidt

Blair A Smith

David J Bombara

Charles Bryce Graves

Jeffrey D Melman

Tara Grant Schetzel

Russell N Bennett

Jason Lawrence

Patrick Louis Clavette

Gregory E Reinhardt

Matthew R Gold

John E Holowczak

Joseph P Lamusga

Xuemei Wang

Lisa A Prill

Aleksander Kojovic

Rick Uskert

Matt Brandt

Jeffery R Schaff

Simon James Jones

Scott Nelson

Daniel A Mosher

Bruce Edward Varney

Kang N Lee

Roderick M Townes

Robert J Shinavski

Paul F Croteau

Matthew T Kush

Steven Hillier

Michael K Sahm

Taylor K Blair

Aleksandar Kojovic

John Alan Weaver

Joseph Gordon Doyle

Robert Alexander Sean Golden

Stuart S Ochs

Emil R Dejulio

Paul Antony Davis

Lee A Hoffman

Bradley C Johnson

Steffan Brown

Matthew Eric Hancock

Steven Clarke

Gregory John Kenneth Harrington

Glenn N Levasseur

Michael Jacquinto

Wesley Thibault

Eric Carreras

Sean Kroszner

Brad D Belcher

Brandon Anderson

David C Jamon

Steve Lozyniak

Michael T Weber

Connic Bird

Jeffrey R Schaff

Todd Z Engel

Gregory Harrington

David Thomas

Richard S Tuthill

Lev A Prociw

In some examples, an article includes a ceramic or a ceramic or ceramic matrix composite (CMC) substrate; and an abradable coating on the CMC substrate. The abradable coating includes a plurality of first rare earth (RE) silicate layers in an alternating arrangement with a plurality of second RE silicate layers, wherein the first RE silicate layers include a rare earth monosilicate and the second RE silicate layers include a rare earth disilicate, and wherein the first RE silicate layers include a greater concentration of the rare earth monosilicate than the second RE silicate layers.

CMAS-resistant abradable coatings

An article may include a substrate, such as a silicon-containing ceramic matrix composite, an environmental barrier coating (EBC) layer on the substrate, and a CMAS-resistant EBC layer on the EBC layer. The EBC layer may include at least one rare-earth disilicate (REDS). The CMAS-resistant EBC layer may include at least one rare-earth monosilicate (REMS) configured to react with CMAS to form crystalline reaction products. The CMAS-resistant EBC layer may include a plurality of vertical cracks extending from a surface of the CMAS-resistant EBC layer at least partially into the CMAS-resistant EBC layer. Additionally, or alternatively, the EBC layer may include a plurality of vertical cracks extending from a surface of the EBC layer into at least a portion of the EBC layer.

CMAS-resistant environmental barrier coating system

In one example, a method for forming a coating system including an environmental barrier coating (EBC) and abradable coating on a substrate. The method may include depositing the EBC on a ceramic or ceramic matrix composite (CMC) substrate to form an as-deposited EBC; heat treating the as-deposited EBC following the deposition of the as-deposited EBC on the substrate to form a heat treated EBC; and subsequently depositing an abradable coating on the heat treated EBC to form an as-deposited abradable coating. The as-deposited abradable coating may be heat treated to form a heat treated abradable coating.

Post deposition heat treatment procedures for EBC and abradable coating on ceramic or CMC substrate

A method may include positioning an eddy current probe proximate to a coated portion of an article. The coated portion of the article includes a conductive substrate and a ceramic coating overlying the conductive substrate. The method includes generating, using the eddy current probe, a first primary magnetic field to induce eddy currents in the coated portion of the article and measuring, using the eddy current probe, a strength of a first secondary magnetic field created by the eddy currents in the coated portion of the article to obtain a first secondary magnetic field measurement. The method includes determining, by a computing device, one or more properties or one or more changes in properties of the article based on the first secondary magnetic field measurement.

Nondestructive profiling of articles including ceramic coatings on conductive substrates

The disclosure describes articles and techniques that include an airfoil having a hybrid coating system to provide improved particle impact resistance and improve CMAS attack resistance on the pressure side of the airfoil and improved thermal load protection on the suction side of the airfoil. An example article for a gas turbine engine may include a substrate, and a hybrid environmental barrier coating (EBC) including a relatively dense EBC layer on a first portion of the substrate and a relatively porous EBC layer on a second portion of the substrate, where the first portion of the substrate is different from the second portion of the substrate, and wherein at least a portion of the relatively porous EBC layer overlaps at least a portion of the relatively dense EBC layer in an overlap region.

Hybrid airfoil coatings

An example article includes a substrate and a barrier coating on the substrate extending from an inner interface facing the substrate to an outer surface opposite the inner interface. The barrier coating includes a bulk matrix and a plurality of discrete plugs inset within the bulk matrix and dispersed across the outer surface of the barrier coating. An example technique includes forming the barrier coating on the substrate of a component.

Barrier coatings

In one example, an article including a metallic substrate; and an abradable coating on the metallic substrate, the abradable coating including a plurality of abradable layers in an alternating arrangement with a plurality of CMAS resistant layers, wherein the plurality of CMAS resistant layers are configured to react with molten CMAS to form a stable phase.

An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.

Multilayer abradable coatings for high-performance systems

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.

Method of forming a boron nitride (BN) nanotube interface coating on ceramic fibers

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.

Preforms system for CMC blades

An article includes a substrate defining a surface, a bond coat on the surface of the substrate, a coating layer on the bond coat, and a wear indicator. The coating layer includes at least one of an environmental barrier coating (EBC) or an abradable coating. The wear indicator disposed in a first region of the coating layer and includes at least one chromophore dopant and a material of the EBC or the abradable coating. The wear indicator is configured to indicate wear of the coating layer.

CMCs with luminescence environmental barrier coatings

In some examples, a component includes a substrate and a non-continuous abradable coating on the substrate. The abradable coating includes a first portion defining a first plurality of coating blocks, a second portion defining a second plurality of coating blocks, and a blade rub portion extending between the first portion and the second portion and defining a third plurality of coating blocks. At least one of the first plurality of coating blocks or the second plurality of coating blocks is different than the third plurality of coating blocks in at least one coating block parameter.

Non-continuous abradable coatings

A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.

Shell and tiled liner arrangement for a combustor

A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

Brazed blade track for a gas turbine engine

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.

Method of processing a ceramic matrix composite (CMC) component

Growing community of inventors

Carmel, IN, United States of America

Jun Shi