United Technologies Corporation

Rtx Corporation

Raytheon Technologies Corporation

Pratt-whitney Canada Corp

David A Litton

Michael J Maloney

Kevin W Schlichting

James W Neal

Brian T Hazel

Melvin Freling

John G Smeggil

David B Snow

Brian S Tryon

Benjamin Joseph Zimmerman

Mladen F Trubelja

Eric M Jorzik

Russell Albert Beers

James Thompson Beals

Xia Tang

Nicholas E Ulion

Christopher Masucci

Sergei F Burlatsky

Mario P Bochiechio

Dmitri Novikov

Richard Wesley Jackson, Iii

Sunil Govinda Warrier

Joseph A DePalma

Christopher W Strock

Alan David Cetel

Robert A White, Iii

Venkatarama K Seetharaman

Joshua E Persky

Elisa M Zaleski

Peter F Gero

Joel Larose

Edward F Pietraszkiewicz

Bryan P Dube

David Ulrich Furrer

John D Riehl

Xuan Liu

Richard Wesley Jackson

Douglas Michael Berczik

Daniel S Rogers

Dinesh K Gupta

Gajawalli V Srinivasan

Sudhangshu Bose

John F Blondin

Zhigang Wang

Glenn A Cotnoir

Neil B Ridgeway

Kaylan M Wessels

Timothy J Harding

Heather Ann Terry

Ahmed Abdillahi Abdi

David L Lambert

David A Lambert

Dmitri L Novikov

Christopher W Shrock

Shiela R Woodward

Edward F Petraszkiewicz

Heather A Terry

David Snow

Kevin W Schlichtung

An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix. At least about 10% of the gettering particles are in a crystalline phase. The article also includes a top coat. An article is also disclosed.

Environmental barrier coating with thermal properties

An adaptive surface texturing method is provided for use with a part formed of ceramic matrix composites (CMCs) to be coated with an environmental barrier coating (EBC). The method includes coating a CMC surface of the part with an initial coating, determining a contour and an undulation pattern of the CMC surface and designing a texturing pattern to follow the contour and the undulation pattern and to be formed in the initial coating based on a thickness of the initial coating and an average particle size of a slurry of the EBC.

Adaptive surface texturing for ceramic matrix composites

A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a substrate, a thermal barrier coating deposited on at least a portion of the substrate, and an outer layer deposited on at least a portion of the thermal barrier coating. The outer layer can include a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer.

Thermal barrier coating for gas turbine engine components

A deposition apparatus () comprising: a chamber (); a process gas source () coupled to the chamber; a vacuum pump () coupled to the chamber; at least two electron guns (); one or more power supplies () coupled to the electron guns; a plurality of crucibles () positioned or positionable in an operative position within a field of view of at least one said electron gun; and a part holder () having at least one operative position for holding parts spaced above the crucibles by a standoff height H. The standoff height H is adjustable in a range including at least 22 inches.

Deposition apparatus and methods

A method of repairing a nonconforming article includes applying a machinable coating to an article with a nonconformance. The article includes a preform at least partially infiltrated with a matrix material, to form a repaired article. The method also includes machining the machinable coating and completing infiltration of the repaired article with the matrix material. A method of repairing an article is also disclosed.

Article and method of making an article by chemical vapor infiltration

A coating-substrate combination includes: a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; and a coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any.

Oxidation-resistant coated superalloy

An environmental barrier coating includes a barrier layer which includes a matrix, diffusive particles, and gettering particles; and a calcium-magnesia alumina-silicate (CMAS)-resistant component. The CMAS-resistant component includes hafnium silicate and a rare earth hafnate. An article and a method of fabricating an article are also disclosed.

Environmental barrier coating

A ceramic matrix composite component includes a ceramic matrix composite wall; a coating disposed on the wall; and a cooling hole formed in the wall. The cooling hole has a metering section defined along a first axis and a diffuser section defined along a second axis that is offset from the first axis. The cooling hole has a total length defined along the first axis, the total length being the sum of a length of the metering portion and a length of the diffuser portion. The length of the metering portion is between about 40 percent and about 85 percent of the total length. A ceramic matrix composite airfoil and a method of applying a coating to a ceramic matrix composite component are also disclosed.

Ceramic matrix composite article and method of making the same

A section of a gas turbine engine includes a ceramic component and a metallic component situated adjacent the ceramic component. The ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface between the ceramic component and a metallic component and a mullite-based coating disposed at the interface. The coating provides thermal protection to the ceramic component and the metallic component, and provides thermochemical protection against interaction between the ceramic component and the metallic component. A gas turbine engine and a method of protecting components in a gas turbine engine are also disclosed.

Machinable coating with thermal protection

An apparatus for use in a coating process includes a chamber, a crucible configured to hold a coating material in the chamber, an energy source operable to heat the interior of the chamber, a coating envelope situated with respect to the crucible, and at least one gas manifold located near the coating envelope. The at least one gas manifold is configured to provide a gas screen between the coating envelope and the crucible.

Apparatus for use in coating process

A deposition apparatus comprises: an infeed chamber; a preheat chamber; a deposition chamber; and optionally at least one of a cooldown chamber and an outlet chamber. At least a first of the preheat chamber and the cooldown chamber contains a buffer system for buffering workpieces respectively passing to or from the deposition chamber.

Deposition apparatus methods for sequential workpiece coating

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 metal silicide phase, a crystalline ceramic phase and an amorphous ceramic phase, wherein the metal silicide phase has an aspect ratio greater than 1:1 but less than 50:1.

Multi-environmental barrier coating, processes for coating articles, and their coated articles

A system for depositing coating on a workpiece includes a deposition chamber within which is formed a vortex to at least partially surround a workpiece therein.

Nanoparticle formation mitigation in a deposition process

Growing community of inventors

West Hartford, CT, United States of America

David A Litton