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STAGED FUEL AND AIR INJECTION IN COMBUSTION SYSTEMS OF GAS TURBINES

United States Patent Application

20170175635
A1
View the Complete Application at the US Patent & Trademark Office
A gas turbine that includes a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section that corresponds to the aftward annulus section and a forward intake section that corresponds to the forward annulus section. The air directing structure may be configured to: direct air entering through the aftward intake section through the aftward annulus section in a forward direction to the staged injector; and direct air entering through the forward intake section through the forward annulus section in a forward direction to the forward injector.
Hughes, Michael John (Pittsburgh, PA), Berry, Jonathan Dwight (Simpsonville, SC)
14/ 978,006
December 22, 2015
FEDERAL RESEARCH STATEMENT [0001] This invention was made with Government support under Contract No. DE-FC26-05NT42643, awarded by the Department of Energy. The Government has certain rights in the invention.