System for supplying fuel to a combustor
AssigneeGeneral Electric Company
InventorsWei Chen, Richard Martin DiCintio, Hasan Karim, Ilya Alexandrovich Slobodyanskiy
Life of this patent
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Abstract
A system for supplying fuel to a combustor includes a combustion chamber and a liner that circumferentially surrounds at least a portion of the combustion chamber. A plurality of fuel nozzles are radially arranged across the combustor upstream from the combustion chamber to supply a swirling flow of fuel into the combustion chamber. A first fuel injector downstream from the plurality of fuel nozzles provides fluid communication for fuel to flow through the liner and into the combustion chamber. The first fuel injector is circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.
Claims20
A system for supplying fuel to a combustor, comprising:
- a. a combustion chamber;
- b. a liner that circumferentially surrounds at least a portion of the combustion chamber;
- c. a plurality of fuel nozzles radially arranged across the combustor upstream from the combustion chamber, wherein the plurality of fuel nozzles supply a swirling flow of fuel into the combustion chamber;
- d. a first fuel injector downstream from the plurality of fuel nozzles, wherein the first fuel injector provides fluid communication for fuel to flow through the liner and into the combustion chamber;
- and
- e. wherein the first fuel injector is circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.
A system for supplying fuel to a combustor, comprising:
- a. a combustion chamber;
- b. a liner that circumferentially surrounds at least a portion of the combustion chamber;
- c. a plurality of fuel nozzles radially arranged across the combustor upstream from the combustion chamber, wherein the plurality of fuel nozzles supply a swirling flow of fuel into the combustion chamber;
- d. a first set of fuel injectors circumferentially arranged around the liner downstream from the plurality of fuel nozzles, wherein the first set of fuel injectors provide fluid communication for fuel to flow through the liner and into the combustion chamber;
- and
- e. wherein the first set of fuel injectors are circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.
A gas turbine, comprising:
- a. a compressor;
- b. a combustor downstream from the compressor;
- c. a turbine downstream from the combustor;
- d. a plurality of fuel nozzles radially arranged inside the combustor;
- e. a combustion chamber downstream from the plurality of fuel nozzles, wherein the plurality of fuel nozzles supply a swirling flow of fuel into the combustion chamber;
- f. a first set of fuel injectors circumferentially arranged around the combustion chamber downstream from the plurality of fuel nozzles, wherein the first set of fuel injectors provide fluid communication for fuel to flow into the combustion chamber;
- and
- g. wherein the first set of fuel injectors are circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.
Dependencies are inferred from the claim text.