Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Agnieszka M Wusatowska-Sarnek

Christopher W Strock

Tahany Ibrahim El-Wardany

Pantcho P Stoyanov

Thomas D Kasprow

Sergei F Burlatsky

David Ulrich Furrer

Jason Elliott

Shaoluo L Butler

Prabir R Bhowal

Larry G Housefield

Ruston M Moore

John Palitsch

Promila Bhaatia

Kevin Seymour

Enrique E Montero

Daniel Anthony Grande

Ronald S Mace

Harpreet Wasan

John M Wezalis

James S Guest

Adam Cade Wilcox

Ryan Clifford Cox

J Michael McQuade

An apparatus for backward flow forming a material may comprise a mandrel having a headstock at a proximate end of the mandrel, the mandrel configured to rotate about an axis, a plurality of rollers disposed radially outward of the mandrel configured to exert force on the material to form a work piece at a plastic deformation zone, wherein the work piece flows from the plastic deformation zone between the plurality of rollers and the mandrel toward a distal end of the mandrel, and a catcher, coaxial to the mandrel, and removably coupled to the work piece at a traveling end of the work piece.

Systems and methods for improving backward flow forming of shafts

Disclosed herein is an article comprising a substrate; an abrasive coating disposed on the substrate; where the abrasive coating comprises a matrix having abrasive grit particles dispersed therein; and a layer of material disposed on the abrasive coating; where the layer of material is a titanium nitride (TiN), boron nitride (BN), titanium-aluminum-nitrides [(TiAl)N], titanium-aluminum-silicon-nitrides [(TiAlSi)N], chromium nitrides (CrN), aluminum oxide (AlO), titanium oxide (TiO), silicon carbo-nitride (SiCN), titanium carbo-nitride (TiCN), or a combination thereof.

Wear resistant coating, method of manufacture thereof and articles comprising the same

A gas turbine engine according to an exemplary aspect of this disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The gas turbine engine further includes a seal assembly including a static structure and a rotatable structure configured to meet to form a contact area. The seal assembly includes an abradable coating on one of the static structure and the rotatable structure, and the seal assembly further includes a cutter on the other of the static structure and the rotatable structure.

Gas turbine engine including seal assembly with abradable coating and cutter

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly includes an abradable coating adjacent the contact area, and the abradable coating includes magnetic particles.

Gas turbine engine including seal assembly with abradable coating including magnetic particles

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly further includes an abradable coating adjacent the contact area. The abradable coating includes magnetic particles embedded in a polymer material.

Gas turbine engine including seal assembly with abradable coating including magnetic particles embedded in polymer

A multilayer abradable coating includes at least one first abradable layer; and at least one second abradable layer, wherein the first abradable layer and the second abradable layer have different properties related to erosion resistance.

Multilayer abradable coating

A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

Wear resistant airfoil tip

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

Wear resistant turbine blade tip

A method for preventing powder depletion/contamination during a consolidation process provides a can for holding a powdered material; the can having an interior wall; a protective layer is positioned intermediate the powdered material and the interior wall utilizing a sol-gel process utilizing monodisperse nanopowders; and the protective layer being formed from a material selected from the group consisting of nickel alloys, chrome alloys, and combinations thereof.

Method for preventing powder depletion/contamination during consolidation process

An embodiment of a gas turbine engine component includes an abrasive coating disposed on at least a portion of a sealing region. The abrasive coating includes an inner abrasive region disposed outward of the sealing region in a coating thickness direction, and an outer abrasive region disposed outward of the inner abrasive region in the coating thickness direction. The inner abrasive region includes abrasive particles retained in an inner matrix, and the outer abrasive region includes abrasive particles retained in an outer matrix. At least one of the inner matrix and the outer matrix is modified with a first indicator material. At least one aspect of the first indicator material corresponds to a thickness range of the abrasive coating being within the inner thickness region or the outer thickness region.

Air seal abrasive coating and method

A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer system comprising a plurality of layers including a relatively erosion-resistant first layer atop a relatively abradable second layer.

Outer airseal abradable rub strip

A rotor for a turbomachine is provided which includes a hub; and a plurality of blades extending radially from the hub, the plurality of blades comprising a first subset of blades having first tips and an abrasive coating on the first tips, and a second subset of blades having second tips with no abrasive coating on the second tips, wherein a radius (R) of the first subset of blades, including thickness of the abrasive coating, is greater than a radius (R) of the second subset of blades, and wherein a base radius (R) of the first subset of blades, not including thickness of the abrasive coating, is less than the radius (R) of the second subset of blades.

Growing community of inventors

Mansfield Ctr., CT, United States of America

Agnieszka M Wusatowska-Sarnek