| CPC F23R 3/346 (2013.01) [F23R 3/286 (2013.01); F23R 3/34 (2013.01); F23R 3/06 (2013.01); F23R 3/283 (2013.01)] | 20 Claims |
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1. An axial fuel stage (AFS) injector for a combustor of a gas turbine (GT) system, the AFS injector comprising:
a mixing member including a mixing chamber defined therein, the mixing chamber having an inlet and an outlet, wherein the outlet is configured to be in fluid communication with a combustion chamber of the combustor;
a high pressure (HP) air-fuel injection member including at least one row of HP air-fuel injectors for directing an air-fuel mixture into the mixing chamber, each HP air-fuel injector including:
an inner wall defining an inner HP air jet conduit therein;
an outer wall surrounding and concentric with the inner wall, wherein the inner wall and the outer wall define an outer HP air jet loop therebetween;
a plurality of spacer members spacing the inner wall from the outer wall; and
a plurality of fuel injector passages extending from an outer surface of the outer wall, through the plurality of spacer members and the inner wall to the inner HP air jet conduit, each fuel injector passage having a first end open at the outer surface of the outer wall and a second end including a fuel injector directed into the inner HP air jet conduit defined by the inner wall; and
a fuel plenum defined in the HP air-fuel injection member and in fluid communication with the first end of each fuel injector passage, the fuel plenum configured to deliver a fuel from a fuel source to each of the fuel injectors,
wherein each inner HP air jet conduit and each HP air jet loop are configured to direct a HP air flow from a HP air source with the fuel into the inlet of the mixing chamber.
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