Apparatus for decreasing combustor emissions
AssigneeGeneral Electric Company
InventorsJagdish Dullabhbhai Mistry, James William Stegmaier
Life of this patent
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Abstract
A combustor for a gas turbine engine includes a fuel delivery system that uses circumferential fuel staging. The fuel delivery system includes a plurality of fuel supply rings and a backpurge sub-system. The fuel supply rings are arranged concentrically at various radial distances to supply fuel to a combustor through a plurality of combustor manifolds and pigtails. The backpurge system uses high temperature and high pressure combustor air to purge fuel from non-flowing fuel supply rings, combustor pigtails, and combustor manifolds. Additionally, the fuel delivery system includes at least two orifices to minimize pressure decays during filling stages.
Claims6
A gas turbine engine comprising:
- a combustor;
- and
- a fuel delivery system comprising a plurality of fuel supply rings, at least one heat exchanger coupled to at least one of said plurality of fuel supply rings, and a backpurge system, said plurality of fuel supply rings configured to supply fuel to said combustor, said backpurge system in flow communication with said plurality of fuel supply rings and said combustor for using combustor air pressure for purging fuel from said fuel delivery system.
Dependencies are inferred from the claim text.