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Combustor Apparatus for Use in a Gas Turbine Engine

United States Patent Application

View the Complete Application at the US Patent & Trademark Office
A combustor apparatus for use in a gas turbine engine. The combustor apparatus includes a liner, a flow sleeve, and a fuel injection system. The liner includes an inner volume, wherein a portion of the inner volume defines a main combustion zone. The flow sleeve receives compressed air, is positioned radially outward from the liner, and includes a forward end and an aft end. The fuel injection system is coupled to the flow sleeve and provides fuel into the inner volume of the liner downstream from the main combustion zone. The fuel injection system includes a fuel manifold and a fuel dispensing structure. The fuel manifold is coupled to the flow sleeve and includes a cavity for receiving fuel. The fuel dispensing structure is associated with the cavity and distributes fuel from the cavity to the liner inner volume.
Fox, Timothy A. (Hamilton, CA), Wiebe, David J. (Orlando, FL)
12/ 477,397
June 3, 2009
[0002] This invention was made with U.S. Government support under Contract Number DE-FC26-05NT42644 awarded by the U.S. Department of Energy. The U.S. Government has certain rights to this invention.