Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Scott A Elliott

Frank J Trzcinski

Andrew Cervoni

Timothy William Quinn

San Quach

John S Tu

Monica Pacheco-Tougas

Robert M Sonntag

John J Rup, Jr

Jeffrey Leon

Joseph James Sedor

Anthony Van

Neil B Ridgeway

Robert Selinsky, Jr

Gerard V Cadieux

Lisa A Jenkins

Lisa Tse

A method of coating a component includes attaching the component to a support that is configured to hold a plurality of components and placing a base of the support in a holder that is attached to rotatable member of a fixture, wherein an axis of the holder is parallel to an axis of rotation of the rotatable member. The method also includes transporting the fixture into a coating chamber wherein a direction of an exit stream of a coater in oriented perpendicularly to the axis of rotation, exposing the fixture and the component to a reverse transfer arc cleaning/pre-heating procedure, and exposing the fixture and the component to a coating procedure during which a coating is directed at the component in a direction perpendicular to the axis of rotation while the rotatable member is rotating. The method further includes transporting the fixture and removing the component from the support fixture.

Metallic coating process for combustor panels using a barrel configuration

A fixture assembly for supporting workpieces in a coating process includes a shaft; and a plurality of fixtures each having a workpiece support surface and a shaft mount defining a shaft mounting structure, wherein the shaft mounting structure extends from the workpiece support surface such that, when the shaft mounting structure is engaged with the shaft, workpiece support surfaces of the fixtures are positioned facing radially outwardly away from the shaft.

Fixture assembly for coating combustor panels

A fixture for masking a gas turbine engine blade, the blade having a root, a platform and an airfoil, the platform having inner and outer surfaces and peripheral faces extending between the surfaces, the fixture including a base with a receptacle for receiving the root of the blade; a removable sidewall mountable to the base to form a masking box with the receptacle that shields the root; a first removable Z plane detail mountable to the base, the first removable Z plane detail providing a first electrical contact point to the root; and a second removable Z plane detail mountable to the removable sidewall, the second removable Z plane detail providing a second electrical contact point to the root

Apparatus and method for masking under platform areas of airfoil components

A fixture for masking a gas turbine engine blade, the blade having a root, a platform and an airfoil, the platform having inner and outer surfaces and peripheral faces extending between the surfaces, the fixture including a base with a receptacle for receiving the root of the blade; a removable sidewall mountable to the base to form a masking box with the receptacle that shields the root; a first removable Z plane detail mountable to the base, the first removable Z plane detail providing a first electrical contact point to the root; and a second removable Z plane detail mountable to the removable sidewall, the second removable Z plane detail providing a second electrical contact point to the root.

A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

Wall panel assembly for a gas turbine engine

Growing community of inventors

Rock Hill, NY, United States of America

Scott A Elliott