United Technologies Corporation

Raytheon Technologies Corporation

Kaitlin M Tomeo

San Quach

Brian T Hazel

John P Rizzo, Jr

John S Tu

Alan C Barron

Henry H Thayer

William F Werkheiser

Aaron S Butler

Jessica L Serra

Bartolomeo Palmieri

Robert Selinsky, Jr

Christopher J Millea

A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.

Combustor panel for gas turbine engine

A method of polishing an outer surface of a ceramic coated gas turbine engine component includes applying a rotating diamond brush to the outer surface. The brush is configured to achieve a uniform finish of 150 microinches Ror less over the surface. The brush contains diamond impregnated bristles, and is affixed to a rotary head of a robotic arm. A force sensing controller limits brush forces against the component. The component disclosed is a hot section turbine vane designed for directional control of high temperature, high-pressure combustion gases, but the method may be applied to other components contained within such aerospace applications. The polished coating provides an improved thermal barrier for maintaining structural integrity of the component in environments having temperatures ranging up to 2,000 degrees Celsius. The method limits abrasive removal of ceramic material to only 0.0005 to 0.00075 inch, and saves time and expense over past practices.

Ceramic coating polishing method

Growing community of inventors

Ellington, CT, United States of America

Kaitlin M Tomeo