1. A fuel flow control system for use in a gas turbine, comprising: a fuel source; at least one manifold coupled with the fuel source; a plurality of nozzles near an end of the manifold that allow fuel to exit the manifold; a plurality of solenoid valves associated with the manifold between the nozzles and the fuel source; and a controller that selectively opens and closes the solenoid valves, respectively, to provide a desired amount of fuel flow through the nozzles.