United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Christopher W Strock

Paul M Lutjen

Changsheng Guo

Shahram Amini

Susan M Tholen

Kevin Seymour

Matthew E Bintz

James Olaf Hansen

Charles R Beaudoin

Robert D Richard

Michael J Maloney

Sergei F Burlatsky

Dmitri Novikov

Steven G Lemay

David A Litton

Brian T Hazel

Melvin Freling

Jose R Paulino

Pantcho P Stoyanov

Russell Albert Beers

Paul Henry Zajchowski

Xuan Liu

Weina Li

Paul W Baumann

Thomas D Kasprow

Michael J Bruskotter

William J Joost

Philip R Belanger

Charles G Davis

Frank W Mase

Thomas E Lang

Richard M Kabara

Kevin C Seymour

Sergey Mironets

Mark R Jaworowski

Aaron T Nardi

Kevin W Schlichting

Alexander Staroselsky

Enzo DiBenedetto

John A Sharon

Michael A Klecka

John R Farris

Thomas J Martin

Benjamin Joseph Zimmerman

Philip Robert Rioux

Thomas J Watson

Agnieszka M Wusatowska-Sarnek

Richard Wesley Jackson, Iii

Donn Blankenship

Nicholas R Leslie

Yan Chen

Imelda P Smyth

George H Reynolds

Ken Robert Lagueux

Promila Bhaatia

John F Corini

Joseph G Pilecki, Jr

Charles R Beaudion

Dale R Doucette

Thomas W Stowe

Gene Buchina

Kara J Bridges

A coated article () includes a substrate () and a coating () on the substrate. The coating includes at least a first layer (). The first layer has: a matrix (); and a filler () at 2.0% to 40% by volume in the first layer. The first layer is selected from alkaline earth or transition metal (M) tungstates (MWO4); alkaline earth molybdates (MMoO); rare earth (RE) phosphates (REPO); and combinations thereof.

Dislocator chemistries for turbine abradable or machinable coating systems

A turbine engine has: a first member () having a surface bearing an abradable coating, the abradable coating () being at least 90% by weight ceramic; and a second member () having a surface bearing an abrasive coating. The abrasive coating () has a metallic matrix () and a ceramic oxide abrasive () held by the metallic matrix, the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating. At least 50% by weight of the ceramic abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.

Turbine engine abradable systems

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

In a method for forming an abradable material (), the abradable material has at least 20% by volume rutile titania () and hBN (). The method includes: blending a first titania powder having an oxygen debit of at least 5.0% with a second titania powder having an oxygen debit, if any, of less than 1.0%. The blend is thermal sprayed. The sprayed blend is then oxidized.

A method () for applying a coating to a substrate () includes spraying () an aluminum-based coating layer () on the substrate. The coating layer is then infiltrated () with an aqueous solution (). The solution comprises: a source of chromium; and potassium hexafluorozirconate.

Solution based corrosion inhibitors for aluminum alloy thermal spray coatings

A blade includes an airfoil section extending between leading and trailing edges, first and second opposed sides each joining the leading and trailing edges, and an inner end and a free end. The blade also includes an abrasive tip at the free end of the airfoil section. The abrasive tip includes particles disposed in a matrix material. The matrix material is a polymeric material that has a glass transition temperature greater than or equal to about 225 degrees C. (437 degrees F.). A gas turbine engine and a method of fabricating a blade are also disclosed.

Blade with abrasive tip

A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.

Fusible bond for gas turbine engine coating system

A novel method of depositing grit particles onto a fan blade tip coating is provided. The method enhances grit capture by presenting a softened coating surface for the impinging particles. The softened surface is achieved without high substrate temperatures that could degrade the base metal properties in the fan blade. An auxiliary heat source is used to establish a locally heated and softened surface where the grit deposition takes place. The softened surface greatly increases the probability of grit capture.

Method of forming an abrasive coating on a fan blade tip

In a method for manufacturing an article, the article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface. Each of the first channels are machined in the body by plunging a rotating bit into the first surface and drawing the rotating bit down the bevel surface. The coating is thereafter applied.

Substrate edge configurations for ceramic coatings

A blade comprises an airfoil having a root end and a tip. A metallic substrate is along at least a portion of the airfoil. An abrasive tip coating comprises an abrasive and an aluminum-based matrix. An aluminum-based base layer is between the tip coating and the substrate.

Abrasive tip blade manufacture methods

An abrasive coating for a substrate including a metallic based bond coat layer; a top layer; and an intermediate layer between the metallic based bond coat layer and the top layer. A method of applying an abrasive coating including applying a metallic based bond coat layer onto a substrate; grading an intermediate layer into the metallic based bond coat layer to form a graded transition between the metallic based bond coat layer and the intermediate layer; and grading a top layer into the intermediate layer to form a graded transition between the intermediate layer and the top layer.

Alumina seal coating with interlayer

A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abrasive filler between about 50%-75% by volume of the abrasive coating.

System and method for manufacture of abrasive coating

A process for manufacturing a preformed sheet having geometric surface features for a geometrically segmented abradable ceramic thermal barrier coating on a turbine engine component, the process comprising the steps of providing a preformed sheet material. The process includes forming a partially of geometric surface features in the sheet material. The process includes joining the sheet material to a substrate of the turbine engine component. The process includes disposing a thermally insulating topcoat over the geometric surface features and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the geometric surface features.

Cost effective manufacturing method for GSAC incorporating a stamped preform

An abrasive coating system for a substrate of an airfoil in a turbine engine high pressure compressor, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, the matrix material consisting of unalloyed chromium and unalloyed aluminum distributed throughout the matrix material, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.

Process and material configuration for making hot corrosion resistant HPC abrasive blade tips

A thermal barrier coating disposed on a substrate comprising a plurality of surface features formed on the substrate proximate an inner side of the substrate, each of the plurality of surface features comprising a metallic column having a top with rounded edges; a dense layer disposed in a valley located between each of the plurality of surface features, and the dense layer disposed on the top and covering the rounded edges; a thermally insulating topcoat disposed over the plurality of surface features.

Thermal barrier coating with reduced edge crack initiation stress and high insulating factor

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Kennebunk, ME, United States of America

Christopher W Strock