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Radial flow fuel nozzle for a combustor of a gas turbine

United States Patent

9,383,098
July 5, 2016
View the Complete Patent at the US Patent & Trademark Office
A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold.
Means; Gregory Scott (Simpsonville, SC), Boardman; Gregory Allen (Greer, SC), Berry; Jonathan Dwight (Simpsonville, SC)
GENERAL ELECTRIC COMPANY (Schenectady, NY)
13/ 664,705
October 31, 2012
FEDERAL RESEARCH STATEMENT This invention was made with Government support under grant number DE-FC26-05NT42643-ARRA, awarded by the Department of Energy. The Government has certain rights in this invention.