System and method for delivering fuel to a gas turbine engine

A gas turbine engine comprising:

• a combustor defining one or more first zones and one or more second zones;
• an ignition source configured to initiate a start-up sequence of the gas turbine engine;
• a plurality of injectors circumferentially arranged about the combustor, the plurality of injectors including one or more first injectors and one or more second injectors;
• and
• a system for delivering a fuel, the system including:
• a start fuel circuit configured to be fluidly coupled to the one or more first injectors to facilitate injection of a first quantity of the fuel by the one or more first injectors into the one or more first zones upon activation of the ignition source;
• at least one main fuel circuit configured to be fluidly coupled to the one or more second injectors to facilitate injection of a second quantity of the fuel by the one or more second injectors into the one or more second zones in response to a light-off of the first quantity of the fuel, and
• at least one torch fuel circuit configured to be fluidly coupled to the ignition source of the gas turbine engine.

A system for delivering a fuel to a gas turbine engine, the gas turbine engine having a combustor and a plurality of injectors circumferentially arranged about the combustor, the system comprising:

• a first fuel circuit configured to be fluidly coupled to one or more first injectors of the plurality of injectors to facilitate injection of a first quantity of the fuel by the one or more first injectors into one or more first zones of the combustor upon activation of an ignition source of the gas turbine engine;
• a second fuel circuit configured to be fluidly coupled to one or more second injectors of the plurality of injectors to facilitate injection of a second quantity of the fuel by the one or more second injectors into one or more second zones of the combustor in response to a light-off of the first quantity of the fuel;
• and
• a third fuel circuit configured to be fluidly coupled to the ignition source of the gas turbine engine,
• wherein the first fuel circuit is connected to a first flow control valve, the second fuel circuit is connected to a second flow control valve, and the third fuel circuit is connected to a third flow control valve.