Method and system for controlling fuel to a dual stage nozzle
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/22
F02C-009/26
F23R-003/34
F23N-001/00
F23D-011/38
출원번호
US-0205963
(2008-09-08)
등록번호
US-8820087
(2014-09-02)
발명자
/ 주소
Ryan, William R.
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
0인용 특허 :
23
초록▼
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
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.
대표청구항▼
1. A method of controlling delivery of fuel to a plurality of duplex nozzles in the combustor of a gas turbine, each duplex nozzle including a primary orifice and a secondary orifice defining an orifice pair, the method comprising: providing a flow divider having a single fuel inlet and a plurality
1. A method of controlling delivery of fuel to a plurality of duplex nozzles in the combustor of a gas turbine, each duplex nozzle including a primary orifice and a secondary orifice defining an orifice pair, the method comprising: providing a flow divider having a single fuel inlet and a plurality of fuel outlets, the flow divider providing a separate positive displacement of fuel to each of the outlets, metering an equal fuel flow in tandem to each of the fuel outlets;providing a single primary fuel supply line connected to each fuel outlet of the flow divider, wherein each primary fuel supply line is separated from fluid communication with any other primary fuel supply line;conveying a liquid fuel from the fuel outlets through each respective primary fuel supply line at a predetermined rate;supplying the fuel from each primary fuel supply line to the primary orifice of a respective duplex nozzle;providing a secondary fuel supply line for each primary fuel supply line, each secondary fuel supply line having an inlet connected to a respective primary fuel supply line between the primary orifice in a respective duplex nozzle and the connection of the primary fuel supply line to a respective fuel outlet of the flow divider, wherein each secondary fuel supply line extends from a respective primary fuel supply line to a secondary orifice in the respective duplex nozzle;providing a valve between the connection of each secondary fuel supply line to a respective primary fuel supply line and a respective secondary orifice;identifying a predetermined operating condition of the gas turbine; andproducing a valve actuating signal in response to identifying the predetermined operating condition, the valve actuating signal effecting actuation of the valves in the secondary fuel supply lines from a closed position to an open position whereby, for each orifice pair, fuel from each primary fuel supply line is conveyed through both the secondary orifice and the primary orifice located in the respective duplex nozzle. 2. The method of claim 1, wherein the flow divider provides a positive displacement of fuel to each of the plurality of primary fuel supply lines to provide fuel at a substantially identical predetermined flow rate. 3. The method of claim 1, wherein the actuation of the valves located on the secondary fuel lines comprises opening of the valves and, following actuation of the valves, a differential pressure at each of the secondary orifices is substantially equal to a differential pressure at the respective first orifice. 4. The method of claim 3, wherein actuation of the valves causes a predetermined decreased differential pressure in the primary fuel supply lines, the decreased differential pressure being above a minimum pressure for effecting atomization of the liquid fuel through both the first orifice and the second orifice. 5. The method of claim 1, wherein the predetermined operating condition comprises a predetermined load on the gas turbine. 6. The method of claim 5, wherein the actuation of the valves located on the secondary fuel lines comprises opening of the valves, and the valves are actuated to close at a second predetermined load on the gas turbine lower than the predetermined load to open the valves. 7. The method of claim 1, wherein the predetermined operating condition comprises a predetermined differential pressure between a pressure in the primary fuel supply lines and a pressure in a combustion zone of the combustor. 8. The method of claim 7, wherein the actuation of the valves located on the secondary fuel lines comprises opening of the valves, and the valves are actuated to close at a second predetermined differential pressure substantially lower than the predetermined differential pressure to open the valves. 9. 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 orifices;providing a second nozzle stage comprising a plurality of secondary orifices, each secondary orifice being associated with a respective primary orifice to form duplex 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 orifices 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 orifices, and each secondary fuel supply line including a valve;identifying a predetermined operating condition of the gas turbine; andproducing a valve actuating signal in response to identifying the predetermined operating condition, the valve actuating signal effecting a sequential actuation of selected groups of valves at predetermined time intervals wherein each selected valve group is defined by a number of valves less than the total number of secondary fuel supply lines and each selected valve group is opened from a closed position at a predetermined time interval following the opening of a prior valve group whereby fuel from each primary fuel supply line is conveyed through corresponding groups of secondary orifices at the predetermined time intervals and wherein the fuel from each primary supply line is also conveyed through the primary orifices. 10. The method of claim 9, wherein the single stage fuel supply comprises a single flow divider, each primary fuel supply line connected to the flow divider and receiving a separate fuel supply from the flow divider, and wherein the flow divider provides a positive displacement of fuel to each of the plurality of primary fuel supply lines to provide fuel at a substantially identical predetermined flow rate. 11. The method of claim 10, wherein the actuation of the valves located on the secondary fuel lines comprises opening of the valves and, following actuation of the valves, a differential pressure at each of the secondary orifices is substantially equal to a differential pressure at the respective first orifice. 12. The method of claim 10, wherein the predetermined operating condition comprises a predetermined differential pressure between a pressure in the primary fuel supply lines and a pressure in a combustion zone of the combustor. 13. The method of claim 12, wherein the actuation of the valves located on the secondary fuel lines comprises opening of the valves, and the valves are actuated to close at a second predetermined differential pressure substantially lower than the predetermined differential pressure to open the valves. 14. The method of claim 9, wherein the predetermined operating condition comprises a predetermined load on the gas turbine. 15. The method of claim 14, wherein the actuation of the valves located on the secondary fuel lines comprises opening of the valves, and the valves are actuated to close at a second predetermined load on the gas turbine lower than the predetermined load to open the valves. 16. The method of claim 9, wherein each of the valves comprises a solenoid valve. 17. 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 orifices;a second nozzle stage comprising a plurality of secondary orifices, each secondary orifice being associated with a respective primary orifice to form an orifice pair located within a duplex nozzle;a plurality of primary fuel supply lines, one of the primary fuel supply lines connected to each of the primary orifices;a flow divider having a single fuel inlet and a plurality of fuel outlets, the flow divider providing a separate positive displacement of fuel to each of the outlets, metering an equal fuel flow in tandem to each of the fuel outlets, wherein a single one of the primary fuel supply lines is connected to each fuel outlet of the flow divider, and each primary fuel supply line is separated from fluid communication with any other primary fuel supply line;the second nozzle stage including a secondary fuel supply line extending from each of the primary fuel supply lines to one of the secondary orifices, each secondary fuel supply line having an inlet connected to a respective primary fuel supply line between the primary orifice in a respective duplex nozzle and the connection of the primary fuel supply line to a respective fuel outlet of the flow divider, wherein each secondary fuel supply line extends from a respective primary fuel supply line to a secondary orifice in the respective duplex nozzle;a valve located in each secondary fuel supply line between a respective secondary orifice and a respective primary fuel supply line;a sensor for identifying a predetermined operating condition of the gas turbine; anda controller for producing a valve actuating signal in response to identifying the predetermined operating condition, the valve actuating signal effecting actuation of the valves in the secondary fuel supply lines from a closed position to an open position whereby, for each orifice pair, fuel from each primary fuel supply line is conveyed through both the secondary orifice and the primary orifice located in a duplex nozzle. 18. The system of claim 17, wherein the flow divider provides a positive displacement of fuel to each of the plurality of primary fuel supply lines to provide fuel at a substantially identical predetermined flow rate. 19. The system of claim 18, wherein each of the valves comprises a solenoid valve.
Beebe Kenneth W. (Galway NY) Davis L. Berkley (Schenectady NY) Iasillo Robert J. (Ballston Spa NY), Fuel trim system for a multiple chamber gas turbine combustion system.
Mandai Shigemi,JPX ; Kawabata Hitoshi,JPX ; Nishida Koichi,JPX, Gas turbine combustor having multiple burner groups and independently operable pilot fuel injection systems.
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