Rtx Corporation

Raytheon Technologies Corporation

United Technologies Corporation

Other

Xuan Liu

Brian T Hazel

William J Brindley

Richard Wesley Jackson

Zhong Ouyang

Andrew DeBiccari

Glenn A Cotnoir

Christopher J Bischof

Danielle E Jencks

James Thompson Beals

Xia Tang

Michael J Minor

Richard Wesley Jackson, Iii

Michael N Task

Brian Richard Craig

Elisa M Zaleski

Kaylan M Wessels

Christopher W Strock

Mark F Zelesky

Kevin W Schlichting

Russell Albert Beers

Adam P Generale

Olivier H Sudre

Russell F Croft

Luke H Rettberg

R Wesley Jackson

Andy Turko

Nicholas M LoRicco

Steven Ivory

Stewart S Fowler

Kathryn Macauley

David A Litton

David Ulrich Furrer

Justin R Hawkes

William F Werkheiser

Max A Kaplan

William J Joost

Rafael A Perez Reisler

Kimberly Marilurene Adams

Randall D Kelton

Arka Ray

Shaun M Enos

Teresa A Munger

Lucy Jean Raymond

Andrew Debiccari

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 process includes applying a slurry to a surface of a metallic article to produce a slurry film on the surface. The slurry is composed of a liquid carrier, chromium and aluminum, and an agent that is reactive with the chromium and aluminum to form intermediary compounds. The article and slurry film are then thermally treated at an activation temperature at which the agent reacts with the chromium and aluminum to form the intermediary compounds. The intermediary compounds deposit the chromium and aluminum on the surface. The thermal treating also diffuses the chromium and aluminum into a sub-surface region of the article such that the sub-surface region becomes enriched with chromium and aluminum.

Aluminum-chromium diffusion coating

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 gas turbine engine component includes a substrate having first surface and a second surface disposed opposite the first surface, a plurality of holes extending through the substrate from the first surface to the second surface, the holes defined by a plurality of respective walls each extending from the first surface to the second surface, a metallic bond coat disposed on the first surface, and an aluminide coating disposed on the first surface, the second surface, and the walls. The metallic bond coat is disposed between the first surface and the aluminide coating and the walls are free of the metallic bond coat.

Internal aluminide coating for vanes and blades and method of manufacture

A method of reducing depletion of elements from an airfoil includes disposing a bond coating on the airfoil, where the airfoil comprises cooling channels. The airfoil includes a material that has an initial composition. A cooling hole is machined in the airfoil to contact the cooling channels such that a fluid travelling in the cooling channel may be discharged via the cooling hole. The machining of the cooling hole results in a formation of a depleted region around the cooling hole. The depleted region is depleted of a portion of the initial composition of the airfoil. A top coat is disposed on the bond coat. The airfoil is subjected to a heat treatment at a temperature effective to promote diffusion of elements from a non-depleted region to the depleted region around the cooling hole.

Method of restoring alloy depletion in an airfoil around cooling holes

An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.

Airfoil having environmental barrier topcoats that vary in composition by location

An article includes a ceramic-based substrate and a barrier layer on the ceramic-based substrate. The barrier layer includes a matrix, diffusive particles, and gettering particles. The gettering particles include at least one of non-gas-evolving particles and porous particles. An article and a method are also disclosed.

Environmental barrier coating

A method for coating a substrate includes spraying a combination of powders. The combination of powders includes: HfSiO; ZrSiO; and, optionally, at least one of HfOand ZrO. A molar ratio of said HfSiOand HfOcombined to said ZrSiOand ZrOcombined is from 2:1 to 4:1. A molar ratio of said HfSiOto said HfOis at least 1:3.

Hafnon and zircon environmental barrier coatings for silicon-based components

A method of repairing a tip for an airfoil is disclosed herein. In various embodiments, the method comprises: removing a portion of the airfoil that reduces a radial height of the airfoil and at least partially removes a defect of the airfoil; removing a remainder of the defect; joining, via gas tungsten arc welding, a filler material to the airfoil to repair the defect; and joining a first mating surface of the airfoil to a second mating surface of a blade tip body via a solid-state joining process.

Systems and methods of hybrid blade tip repair

A coated substrate has a substrate and a coating system having one or more ceramic layers. At least a first layer of one of the one or more ceramic layers is a columnar layer having as-deposited columns and intercolumn gaps. The intercolumn gaps have a mean width at least one of: at least 4.0 micrometers; and at least 1.5% of a thickness of said first layer.

Thermal barrier coating

A method of coating a component including aluminizing an array of internal passageways within the component; and chromizing a portion of the array of internal passageways within the component. A component, including an airfoil having an array of aluminized internal passageways, the array of aluminized internal passageways chromized up to a demarcation.

Process for location-specific slurry based coatings for internally-cooled component

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

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Glastonbury, CT, United States of America

Xuan Liu