Method and System for Controlling Fuel to a Dual Stage Nozzle
AssigneeSiemens Power Generation, Inc.
InventorWilliam R. Ryan
Life of this patent
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Abstract
A method and system for controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine. A liquid fuel is conveyed from a single stage fuel supply through a plurality of primary fuel supply lines to a first nozzle stage including a plurality of primary nozzles. A predetermined operating condition of the gas turbine is identified and a signal is produced in response to the identified operating condition. The signal effects actuation of valves located on secondary fuel supply lines extending from each of the primary fuel supply lines to supply fuel to respective secondary nozzles.
Claims20
A method of controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine, the method comprising:
- conveying a liquid fuel from a single stage fuel supply through a plurality of primary fuel supply lines at a predetermined rate;
- supplying the fuel from the primary fuel supply lines to a first nozzle stage comprising a plurality of primary nozzles associated with the primary fuel supply lines;
- identifying a predetermined operating condition of the gas turbine;
- and
- producing a signal in response to identifying the predetermined operating condition, the signal effecting actuation of a plurality of valves, each valve located on a secondary fuel supply line extending between one of the primary fuel supply lines and a respective secondary nozzle, the secondary nozzles forming a second nozzle stage.
A method of controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine, the method comprising:
- providing a first nozzle stage comprising a plurality of primary nozzles;
- providing a second nozzle stage comprising a plurality of secondary nozzles, each secondary nozzle being associated with a respective primary nozzle to form nozzle pairs;
- conveying a liquid fuel from a single stage fuel supply through a plurality of primary fuel supply lines at a predetermined rate to each of the primary nozzles in the first nozzle stage;
- the second nozzle stage including a secondary fuel supply line from each of the primary fuel supply lines to one of the secondary nozzles, and each secondary fuel supply line including a valve;
- identifying a predetermined operating condition of the gas turbine;
- and
- producing a signal in response to identifying the predetermined operating condition, the signal effecting actuation of the valves whereby fuel from each primary fuel supply line is conveyed through the primary and secondary nozzles of a respective nozzle pair.
A dual stage nozzle fuel control system for providing fuel to the combustor section of a gas turbine, said system comprising:
- a first nozzle stage comprising a plurality of primary nozzles;
- a second nozzle stage comprising a plurality of secondary nozzles, each secondary nozzle being associated with a respective primary nozzle to form a nozzle pair;
- a plurality of primary fuel supply lines, one of the primary fuel supply lines connected to each of the primary nozzles;
- a single stage fuel supply connected to the primary fuel supply lines for supplying fuel to each of the primary fuel lines;
- the second nozzle stage including a secondary fuel supply line extending from each of the primary fuel supply lines to one of the secondary nozzles;
- a valve located in each secondary fuel supply line between a respective secondary nozzle and a primary fuel supply line;
- a sensor for identifying a predetermined operating condition of the gas turbine;
- and
- a controller for producing a signal in response to identifying the predetermined operating condition, the signal effecting actuation of the valves whereby fuel from each primary fuel supply line is conveyed through the primary and secondary nozzles of a respective nozzle pair.
Dependencies are inferred from the claim text.