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AssigneeGeneral Electric Company
InventorsLewis B. Davis, Jr., David O. Fitts, Warren J. Mick, Michael B. Sciocchetti, Mitchell R. Cohen
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A method of operating a combustor for a turbine includes flowing fuel through a symmetrical annular array of fuel nozzles to provide an asymmetrical fuel pattern across the combustor. The asymmetrical fuel flow is provided during a diffusion mode of operation prior to transition between the diffusion mode and a premixed mode of operation, during the transition and during the premixed mode of operation. Near full power, the fuel is supplied equally among the fuel nozzles operating in the premixed mode. The asymmetric fuel flow stabilizes the combustor and inhibits high amplitude combustion noise while achieving low emission operation in the premixed mode.
A method of operating a combustor for a gas turbine wherein the combustor has a plurality of fuel nozzles arranged about an axis of the combustor, comprising the step of variably controlling the flow of fuel through the nozzles to a combustion zone downstream of said nozzles to provide an asymmetric flow of fuel across the combustor in a plane normal to said axis and during transition between a diffusion flow mode of operation and a premixed mode of operation.
A method of operating a combustor for a gas turbine wherein the combustor has a plurality of fuel nozzles in an annular array about an axis of the combustor comprising the step of providing an asymmetric flow of fuel across the combustor in a plane normal to said axis to a combustion zone downstream of said nozzles and during transition between a diffusion flow mode of operation and a premixed mode of operation.
A method of operating a combustor for a gas turbine wherein the combustor has a plurality of nozzles in an array about an axis of said combustor comprising the steps of:
Dependencies are inferred from the claim text.