Gas turbomachine combustor assembly including a liquid fuel start-up system
AssigneeGeneral Electric Company
InventorBorys Borysovich Shershnyov
Life of this patent
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Abstract
A turbomachine combustor assembly includes a combustor body, a combustion chamber defined within the combustor body, one or more combustion nozzles positioned to direct a combustible fluid into the combustion chamber, and a fuel start-up system fluidly connected to the combustion chamber. The fuel start-up system is configured and disposed to combine a liquid fuel and a combustible gas to form an ignition fuel. A pilot nozzle is fluidly connected to the fuel start-up system. The pilot nozzle is configured and disposed to deliver an atomized cloud of the ignition fuel toward the combustion chamber.
Claims20
A turbomachine combustor assembly comprising:
- a combustor body;
- a combustion chamber defined within the combustor body;
- one or more combustion nozzles positioned to direct a combustible fluid into the combustion chamber;
- a fuel start-up system fluidly connected to the combustion chamber, the fuel start-up system being configured and disposed to combine a liquid fuel and a combustible gas to form an ignition fuel;
- and
- a pilot nozzle fluidly connected to the fuel start-up system, the pilot nozzle being configured and disposed to atomize the ignition fuel and deliver an atomized cloud of the ignition fuel toward the combustion chamber.
A method of delivering an atomized pilot fuel into a turbomachine combustion chamber, the method comprising:
- introducing a liquid fuel into an start fuel vessel;
- introducing a combustible gas into the start fuel vessel;
- combining the liquid fuel and the combustible gas in the start fuel vessel to form a liquid ignition fuel;
- passing the liquid ignition fuel to a pilot nozzle;
- and
- discharging an atomized cloud of the liquid ignition fuel from the pilot nozzle into the combustion chamber.
A turbomachine comprising:
- a compressor portion;
- a turbine portion mechanically linked to the compressor portion;
- and
- a combustor assembly including a combustor body, a combustion chamber defined within the combustor body, one or more combustion nozzles positioned to direct a combustible fluid into the combustion chamber, a fuel start-up system fluidly connected to the combustion chamber, the fuel start-up system being configured and disposed to combine a liquid fuel and a combustible gas to form an ignition fuel, and a pilot nozzle fluidly connected to the fuel start-up system, the pilot nozzle being configured and disposed to atomize the ignition fuel and deliver an atomized cloud of the ignition fuel toward the combustion chamber.
Dependencies are inferred from the claim text.