Abstract: A method of starting a gas turbine and related apparatus, the method including keeping a main fuel line in a sealed state while allowing fuel to flow from a fuel source to at least one nozzle of a nozzle array via an auxiliary fuel line; firing a gas turbine while keeping the main fuel line in the sealed state; and after combustion has started: opening the main fuel line to commence a flow of fuel from the fuel source to the at least one nozzle of the nozzle array via the main fuel line, sealing the auxiliary fuel line, and after the auxiliary fuel line is sealed, increasing the flow of fuel from the fuel source to the at least one nozzle of the nozzle array via the main fuel line.

Abstract: A gas turbine drive system in mechanical drive configuration is described. The gas turbine drive system comprises a gas turbine engine drivingly connected to a driven turbomachine. The gas turbine engine includes a dry low NOx emission combustor. A gas turbine controller is further provided. The gas turbine controller is arranged and configured for regulating the combustion temperature according to at least one control parameters of the turbomachine so that a lean blowout of the combustor is prevented when a transient event involving the driven turbomachine occurs.