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Lean-rich axial stage combustion in a can-annular gas turbine engine

United States Patent

June 14, 2016
View the Complete Patent at the US Patent & Trademark Office
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An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method (200) for axial stage combustion in the gas turbine engine (10) is also presented.
Laster; Walter R. (Oviedo, FL), Szedlacsek; Peter (Winter Park, FL)
13/ 739,316
January 11, 2013
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT Development for this invention was supported in part by Contract No. DE-FC26-05NT42644 awarded by the United States Department of Energy. Accordingly, the United States Government may have certain rights in this invention.