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A fuel supply control system for a gas turbine includes a plurality of solenoid valves. The solenoid valves are energized in a timing sequence with a phase relationship designed to achieve a desired fuel flow. In one example, one solenoid valve is associated with a primary portion of a fuel manifold

A fuel supply control system for a gas turbine includes a plurality of solenoid valves. The solenoid valves are energized in a timing sequence with a phase relationship designed to achieve a desired fuel flow. In one example, one solenoid valve is associated with a primary portion of a fuel manifold while at least two other solenoids are associated with a secondary portion of the manifold. A controller that energizes the solenoids to achieve the desired fuel flow can receive feedback information regarding turbine performance to make adjustments to the solenoid operation to bring the turbine performance closer to a desired level.

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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

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; anda controller that selectively opens and closes the solenoid valves, respectively, to provide a desired amount of fuel flow through the nozzles such that a sum total open time for all of the solenoid valves is greater than the time during which fuel flows through the nozzles. 2. The system of claim 1, wherein the controller uses pulse width modulation to control the solenoid valves and wherein a time during which fuel flows through the nozzles is greater than an open time for any one of the solenoid valves during a cycle. 3. The system of claim 1, wherein the manifold includes a first portion and a second portion and wherein at least one of the solenoid valves controls fuel flow through the first portion and at least one other of the solenoid valves controls fuel flow through the second portion. 4. The system of claim 3, wherein there are a plurality of the solenoid valves associated with the second portion. 5. The system of claim 3, wherein the manifold first portion comprises a ring and the second portion comprises a second ring. 6. The system of claim 1, wherein the controller determines a turbine speed and uses the speed information to control the solenoid valves to achieve a desired turbine performance. 7. A fuel flow control system for use in a gas turbine, comprising:a fuel source;at least one manifold coupled with the fuel source, the manifold including a first portion and a second portion;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, a plurality of the solenoid valves associated with the second portion, at least one of the solenoid valves controlling fuel flow through the first portion and at least one other of the solenoid valves controlling fuel flow through the second portion; anda controller that selectively opens and closes the solenoid valves, respectively, to provide a desired amount of fuel flow through the nozzles, the controller selectively opening the solenoid valve associated with the first portion during an engine start up procedure and closing the solenoid valve associated with the first portion during normal engine operation. 8. 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; anda controller that selectively opens and closes each of the solenoid valves within a fuel supply cycle, to provide a desired amount of fuel flow through the nozzles, the controller modifying a phase relationship between the opening and closing different ones of the solenoids for a subsequent fuel supply cycle. 9. A fuel flow control system for use in a gas turbine, comprising:a fuel source;at least one manifold coupled with the fuel source, the manifold having a first portion and a second portion;a plurality of nozzles near an end of the manifold that allow fuel to exit the manifold, at least one of the nozzles being associated with the first portion and at least one other of the nozzles being associated with the second portion;a plurality of solenoid valves associated with the manifold between the nozzles and the fuel source, at least one of the solenoid valves being positioned to control flow between the fuel source and the first portion of the manifold; anda controller that selectively opens and closes the solenoid valves, respectively, to provide a desired amount of fuel flow through the nozzles such th at a sum total open time for all of the solenoid valves is greater than the time during which fuel flows through the nozzles. 10. The system of claim 9, wherein the controller uses pulse width modulation to control the solenoid valves and wherein the a time during which fuel flows through the nozzles is greater than an open time for any one of the solenoid valves during a cycle. 11. The system of claim 9, wherein at least one other of the solenoid valves controls fuel flow through the second portion. 12. The system of claim 11, wherein there are a plurality of the solenoid valves associated with the second portion. 13. The system of claim 9, wherein the manifold first portion comprises a ring and the second portion comprises a second ring. 14. A fuel flow control system for use in a gas turbine, comprising:a fuel source;at least one manifold coupled with the fuel source, the manifold having a first portion and a second portion;a plurality of nozzles near an end of the manifold that allow fuel to exit the manifold, at least one of the nozzles being associated with the first portion and at least one other of the nozzles being associated with the second portion;a plurality of solenoid valves associated with the manifold between the nozzles and the fuel source, at least one of the solenoid valves being positioned to control flow between the fuel source and the first portion of the manifold; anda controller that selectively opens and closes the solenoid valves, respectively, to provide a desired amount of fuel flow through the nozzles, the controller selectively opening the solenoid valve associated with the first portion during an engine start up procedure and closing the solenoid valve associated with the first portion during normal engine operation. 15. A method of controlling fuel flow in a turbine assembly, comprising the steps of:providing a plurality of solenoid valves between a fuel source and a plurality of nozzles associated with a manifold; andcontrolling an open time for each solenoid and a phase relationship between the open times during a cycle such that a sum total of all of the open times is greater than a time during which fuel is flowing through the nozzles and an amount of fuel flow through each solenoid is less than that required during the cycle to achieve a total fuel flow through the solenoids that provides a desired turbine performance. 16. The method of claim 15, including providing at least one solenoid in association with a first portion of a fuel manifold and controlling the at least one solenoid to allow fuel flow only during a turbine start up procedure. 17. The method of claim 15, including overlapping the open times of at least two of the solenoids. 18. The method of claim 15, including determining a current turbine speed and adjusting at least one of the phase relationship or the open times responsive to the determined speed relative to a desired speed. 19. 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 opposite from the fuel source that allow fuel to exit the manifold;a plurality of solenoid valves between the manifold and the fuel source; anda controller that selectively opens and closes the solenoid valves, respectively, such that each solenoid valve opens and closes within a fuel supply cycle and the open time of each solenoid during the fuel supply cycle is less than the time of the fuel supply cycle.