Rtx Corporation

Raytheon Technologies Corporation

United Technologies Corporation

Other

Brian T Hazel

David A Litton

Michael J Maloney

James W Neal

Xuan Liu

Dominic J Mongillo, Jr

James M Koonankeil

Mario P Bochiechio

James Thompson Beals

Xia Tang

Robert A White, Iii

Zhongfen Ding

John A Sharon

Richard Wesley Jackson, Iii

Paul M Lutjen

Raymond C Surace

Matthew A Devore

Kevin W Schlichting

John R Farris

Paul Henry Zajchowski

Michael J Minor

James F Wiedenhoefer

Paul Edward Denney

Christopher W Strock

Jonathan Jeffery Eastwood

Benjamin Joseph Zimmerman

Richard Wesley Jackson

Kevin Zacchera

Henry H Thayer

San Quach

Daniel A Bales

Dennis M Moura

Brian Richard Craig

Elisa M Zaleski

William F Werkheiser

Eric M Jorzik

Jessica L Serra

Kaylan M Wessels

Paul E Denney

Glenn A Cotnoir

Joseph A DePalma

Alan C Barron

Donn Blankenship

Luke H Rettberg

Christopher J Bischof

R Wesley Jackson

Stewart S Fowler

Steven Ivory

Mary Catherine Gurak

Nicholas M LoRicco

Melvin Freling

Russell Albert Beers

John D Riehl

John S Tu

Justin R Hawkes

Olivier H Sudre

Thomas DeMichael

Gajawalli V Srinivasan

Michael N Task

John F Blondin

Tianli Zhu

Zhigang Wang

Mladen F Trubelja

Aaron S Butler

Robert Selinsky, Jr

Kevin Lee Collins

Danielle E Jencks

Kaitlin M Tomeo

Kimberly Marilurene Adams

Craig L Ostrout

Shaun M Enos

Teresa A Munger

Lucy Jean Raymond

Dominic J Mongillo

Christopher W Shrock

Jessica T Serra

A method for coating a component having: a metallic substrate; a ceramic coating having one or more ceramic coating layers atop the substrate; and a cooling passageway system comprising a plurality of feed passageways extending from one or more inlet ports and a plurality of outlet passageways. The outlet passageways have openings in the coating. The method involves: applying a slurry aluminide to the plurality of outlet passageways; coupling the one or more inlets to a suction source; applying an external gas flow to the component, the suction source drawing the external gas in through the outlet passageways and out through the one or more inlet ports, the external gas flow comprising at least 50% by volume combined one to all of Ar, He, and H; and while the suction source is drawing the external gas, heating the component to aluminize the cooling passageway system.

Internal aluminization of coated substrates

A method can comprise forming a component comprising a first mating surface; coupling the component to an airfoil having a second mating surface and a Field Assisted Sintering Technology ('FAST') system; heating, via the FAST system, the airfoil and the component; and applying, via the FAST system, a mechanical pressure between the first mating surface and the second mating surface to join the airfoil to the component and form a blade, the component at least partially defining a leading edge of the blade in response to joining the airfoil to the component

Systems and methods of blade leading edge repair using field assisted sintering technology

A method for coating a metallic substrate includes applying an MCrAlY coating. Machining removes the MCrAlY coating from one or more regions of the substrate. A simultaneous aluminizing and chromizing: aluminizes an interior surface region of the substrate lacking the MCrAlY and at least a portion of a region where the MCrAlY remains; and chromizes an exterior surface region of the substrate lacking the MCrAlY and at least a different portion of the region where the first MCrAlY remains.

Turbine airfoil coating

A method of assembling a part is provided and includes forming a first section of the part, defining, in the first section, passages with dimensions as small as 0.005 inches (0.127 mm), forming a second section of the part, metallurgically bonding the first and second sections whereby the passages are delimited by the first and second sections and executing the metallurgically bonding without modifying a condition of the passages.

Hybrid bonded configuration for blade outer air seal (BOAS)

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 method of forming a coating includes providing a mold that has a flexible wall that defines a mold cavity, inserting a component that is to be coated into the mold cavity, the component having a component surface roughness and there being a coating gap defined between the component and the flexible wall of the mold cavity, introducing a molding slurry into the mold cavity, the molding slurry filling the coating gap and contacting the component so as to overcoat the component surface roughness, solidifying the molding slurry to form a green coating on the component, and consolidating the green coating to form a final coating on the component, the final coating having a coating surface roughness that is less than the component surface roughness.

Method and system for molded coating on CMC

A seal system a ceramic component having a surface region defining a first surface roughness, a metallic component situated adjacent the surface region, and a coating system disposed on the surface region. The coating system includes a silicon-containing layer on the surface region and a barrier layer on the silicon-containing layer. The silicon-containing layer has a surface in contact with the barrier layer. The barrier layer has a surface in contact with the metallic component. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The barrier layer limits interaction between silicon of the silicon-containing layer and elements of the metallic component. The barrier layer has a coefficient of thermal expansion that is within about 60% of a coefficient of thermal expansion of the ceramic component. A gas turbine engine and a method are also disclosed.

Ceramic component having silicon layer and barrier layer

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 gas turbine engine component having a substrate; a thermal barrier coating on the substrate having a porous microstructure; and a reflective layer conforming to the porous microstructure of the thermal barrier coating, wherein the reflective layer comprises a conforming nanolaminate defined by alternating layers of platinum group metal materials selected from the group consisting of platinum group metal-based alloys, platinum group metal intermetallic compounds, mixtures of platinum group metal with metal oxides and combinations thereof. A capping layer can be added over the reflective layer. A supporting layer can be added between the reflective layer and the thermal barrier coating. A process is also disclosed.

Thermally stable thin-film reflective coating and coating process

A calcium-magnesium-alumino-silicate (CMAS)-reactive thermal barrier coating includes a ceramic coating and a CMAS-reactive overlay coating, wherein the CMAS-reactive overlay coating conforms to a surface of the ceramic coating and comprises a compound that forms a stable high melting point crystalline precipitate when reacted with molten CMAS at a rate that is competitive with CMAS infiltration kinetics into the thermal barrier coating. The ceramic coating phase is stable with the CMAS-reactive overlay coating.

Reactive thermal barrier coating

A manufacturing method is provided. During this method, a preform component for a turbine engine is provided that includes a substrate. A meter section of a cooling aperture is formed in the substrate. An external coating is applied over the substrate. At least a portion of the substrate and the external coating is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the substrate and the external coating. A diffuser section of the cooling aperture is formed in the external coating and the substrate based on the scan data.

Forming and/or inspecting cooling aperture(s) in a turbine engine component

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

An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.

Hybrid superalloy article and method of manufacture thereof

Growing community of inventors

Avon, CT, United States of America

Brian T Hazel