United Technologies Corporation

Raytheon Technologies Corporation

Robert Selinsky, Jr

San Quach

John S Tu

Robert M Sonntag

John J Rup, Jr

Anthony Van

Brian T Hazel

Monica Pacheco-Tougas

Randal G McKinney

Jeffrey Leon

Frank J Trzcinski

Joseph James Sedor

William F Werkheiser

Aaron S Butler

George F Titterton, Iii

Jessica L Serra

Scott A Elliott

Neil B Ridgeway

Andrew Cervoni

Gerard V Cadieux

John William Green

Kaitlin M Tomeo

Lisa A Jenkins

Lisa Tse

A combustor panel of a combustor may include a combustion facing surface, a cooling surface opposite the combustion facing surface, and heat transfer pins extending from the cooling surface. A grouping of the heat transfer pins may include a metallic coating.

Systems and methods for combustor panel

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 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

A fuel nozzle guide and method of assembly/disassembly is disclosed with the nozzle guide having a frusto-conical hub section, an annular base, a pair of retaining tabs for securing the guide to the outer wall of a combustor bulkhead for limited movement relative to the bulkhead, and a radial inflow swirler. The method of assembly/disassembly comprises assembling/disassembling the nozzle guide in the bulkhead from the outer wall (cold) side of the bulkhead and mechanically connecting/disconnecting the nozzle guide to/from the outer wall of the bulkhead with mechanical fasteners.

Fuel nozzle guide for gas turbine engine and method of assembly/disassembly

Growing community of inventors

Moodus, CT, United States of America

Robert Selinsky, Jr