United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Raytheon Technologies Coporation

Brandon A Gates

Michael A Morden

William Bogue

James Olaf Hansen

Brian Kenneth Holland

Lee Drozdenko

Scot Adams Webb

Jesse C Meyer

John D Riehl

John Harner

Kerry Lynn Davis

Maria C Kirejczyk

Gary A Wigell

Jonathan Roobol

Richard B Bergethon

John Joseph Marcin

Michael Parkin

Thomas M Morin

Scot A Webb

Mark Quinn

Leland Wiegman

Lee M Drozdenko

Robert M Shemenski

Leland M Wiegman

A drench system includes a rotating mount to rotate a workpiece, a showerhead to dispense a fluid onto the workpiece; and a tray to collect the fluid and recirculate the fluid to the shower. A method of repairing or remanufacturing a coating includes abrading a surface to at least partially remove a portion of a coating to leave an abraded surface; applying a sol-gel over the abraded surface; applying a corrosion resistant primer onto the sol-gel; and applying an erosion coating onto the corrosion resistant primer.

Processes and tooling associated with coating application

Disclosed is a method of repairing a rear cone segment erosion coating including removing a portion of an existing fluoroelastomer coating from a rear cone segment to form a repair area; forming a cured replacement erosion coating corresponding to the repair area, wherein the cured replacement erosion coating has a layer of fluoroelastomer and a layer of fibrous reinforcement; preparing the repair area and the cured replacement erosion coating for adhesion; locating the prepared cured replacement erosion coating on the prepared repair area; and adhering the prepared cured replacement erosion coating to the prepared repair area. Also disclosed is a cured replacement erosion coating and a repaired inlet nose cone.

Fluoroelastomer erosion coating repair

A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.

Fan blade with adhesive fabric stackup

An airfoil member () comprising has a substrate () along at least a portion of an airfoil () of the airfoil member. A sheath () has a channel () receiving a portion () of the substrate. A scrim () is between the substrate and the sheath. A spacer () is between the sheath and the substrate and has a plurality of spaced-apart portions () with gaps between the spaced-apart portions.

Fan blades and manufacture methods

A method for anodizing a bonded assembly may include attaching a first electrode to a first component of the bonded assembly, and forming a first oxide layer on the first component. The bonded assembly may comprise the first component and a second component bonded to the first component. The second component may be electrically isolated from the first component.

Anodization of bonded assembly

An airfoil member () comprising has a substrate () along at least a portion of an airfoil () of the airfoil member. A sheath () has a channel () receiving a portion () of the substrate. A plurality of separate spacers () are between the sheath and the substrate and have a plurality of gaps between the spacers.

A method of remanufacturing a liner panel for a gas turbine engine includes removing a bushing from a damaged component; and molding the bushing with a material charge. A liner panel for a gas turbine engine includes a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel. A liner panel for a gas turbine engine includes a forward fan exit case liner panel molded from a material charge that includes a multiple of layers. At least one of the multiple of layer includes a discontinuity.

Repair or remanufacture of liner panels for a gas turbine engine

An airfoil includes an airfoil body made of a first metal with a leading edge, a trailing edge, pressure side and suction side; a sheath with first and second flanks made of a second metal; a first layer of non-conductive material adhesively bonded between a portion of the end of the first flank and the airfoil body and extending beyond the end of the first flank on the pressure side; and a second layer of non-conductive material adhesively between a portion of the end of the second flank and the airfoil body and extending beyond the end of the second flank on the suction side.

Airfoil with galvanic corrosion preventive shim

Growing community of inventors

DeWitt, MI, United States of America

Brandon A Gates