Systems and methods for controlling the startup of a gas turbine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/22
F02C-007/26
F02C-009/00
F01D-019/00
출원번호
US-0841726
(2010-07-22)
등록번호
US-8955334
(2015-02-17)
발명자
/ 주소
Hansen, Brian Patrick
LaMaster, Christopher Edward
DeJoris, Timothy Edward
Snider, David August
출원인 / 주소
General Electric Company
대리인 / 주소
Sutherland Asbill & Brennan LLP
인용정보
피인용 횟수 :
0인용 특허 :
6
초록▼
Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control a fuel flow provided to a combustor componen
Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control a fuel flow provided to a combustor component associated with the gas turbine. A drive component may be configured to supply a rotational force to a shaft associated with the gas turbine. At least one control device may be configured to (i) direct the gas discharge component to discharge gas from the compressor component, (ii) direct the fuel control component to adjust the fuel flow, and (iii) direct the drive component to rotate the shaft.
대표청구항▼
1. A system for controlling the startup of a gas turbine, the system comprising: a gas discharge component configured to discharge gas from a compressor component associated with the gas turbine;a fuel control component configured to control a fuel flow provided to a combustor component associated w
1. A system for controlling the startup of a gas turbine, the system comprising: a gas discharge component configured to discharge gas from a compressor component associated with the gas turbine;a fuel control component configured to control a fuel flow provided to a combustor component associated with the gas turbine;a drive component configured to supply a rotational force to a shaft associated with the gas turbine; andat least one control device configured to (i) direct the gas discharge component to discharge gas from the compressor component to reduce a compressor pressure ratio associated with the compressor component, (ii) direct the fuel control component to adjust the fuel flow to a value associated with the reduced compressor pressure ratio, and (iii) dynamically direct the at least one motor to provide an increased rotational force to the shaft in response to the reduced compressor pressure ratio induced by the gas discharge component after ignition of the fuel flow. 2. The system of claim 1, wherein the at least one control device directs at least one of the gas discharge component, the fuel control component, or the drive component based upon a fixed schedule associated with the startup of the gas turbine. 3. The system of claim 1, wherein the at least one control device is further configured to identify a desired operating line associated with the compressor component, and wherein the at least one control device directs at least one of the gas discharge component, the fuel control component, or the drive component based upon the identified desired operating line. 4. The system of claim 1, wherein the at least one control device is further configured to calculate, based at least in part on one or more of (i) an amount of gas discharged by the gas discharge component or (ii) the fuel flow provided to the combustor component, a desired torque to be supplied by the drive component, and wherein the at least one control device directs the drive component based upon the calculation of the desired torque. 5. The system of claim 1, wherein the at least one control device is further configured to identify one or more parameters associated with the startup of the gas turbine, and wherein the at least one control device directs at least one of the gas discharge component, the fuel control component, or the drive component based upon the identified one or more parameters. 6. The system of claim 5, wherein the one or more parameters comprise at least one of (i) a time during the startup of the gas turbine at which a rotating stall window associated with the compressor component should be shifted, (ii) a rotational velocity of the shaft during the startup of the gas turbine at which the rotating stall window associated with the compressor component should be shifted, or (iii) a desired fuel to gas ratio for the combustor component. 7. The system of claim 1, wherein the at least one control device directs at least one of the gas discharge component, the fuel control component, or the drive component during a portion of a startup sequence for the gas turbine. 8. The system of claim 1, wherein the discharge of gas and the adjustment in fuel flow shifts a rotating stall window associated with the compressor component. 9. The system of claim 1, wherein the at least one control device is further configured to alter an acceleration schedule associated with the startup of the gas turbine. 10. The system of claim 1, wherein the drive component comprises one of (i) a motor or (ii) a generator that receives power via a load commutated inverter. 11. A method for controlling the startup of a gas turbine, the method comprising: directing a discharge of gas from a compressor component associated with the gas turbine thereby reducing a compressor pressure ratio associated with the compressor component;directing an adjustment of a fuel flow provided to the combustor component associated with the gas turbine to a value associated with the reduced compressor pressure ratio, anddynamically directing the at least one motor to provide an increased rotational force to a shaft in response to the reduced compressor pressure ratio induced by the gas discharge component after ignition of the fuel flow,wherein the above operations are performed by one or more computing devices associated with one or more control devices. 12. The method of claim 11, wherein at least one of directing the discharge of gas, directing the adjustment of the fuel flow, or directing a drive component to supply a rotation force comprises directing based upon a fixed schedule associated with the startup of the gas turbine. 13. The method of claim 11, further comprising: identifying, by the one or more computing devices, a desired operating line associated with the compressor component,wherein at least one of directing the discharge of gas, directing the adjustment of the fuel flow, or directing the drive component is based upon the identified desired operating line. 14. The method of claim 11, further comprising: calculating, by the one or more computing devices based at least in part on one or more of (i) an amount of discharged gas or (ii) the fuel flow provided to the combustor component, a desired torque to be supplied by the drive component,wherein directing the drive component comprises directing the drive component based upon the calculated desired torque. 15. The method of claim 11, further comprising: identifying, by the one or more computing devices, one or more parameters associated with the startup of the gas turbine,wherein at least one of directing the discharge of gas, directing the adjustment of the fuel flow, or directing the drive component is based upon the identified one or more parameters. 16. The method of claim 15, wherein identifying one or more parameters comprises identifying at least one of (i) a time during the startup of the gas turbine at which a rotating stall window associated with the compressor component should be shifted, (ii) a rotational velocity of the shaft during the startup of the gas turbine at which the rotating stall window associated with the compressor component should be shifted, or (iii) a desired fuel to gas ratio for the combustor component. 17. The method of claim 11, wherein at least one of directing the discharge of gas, directing the adjustment of the fuel flow, or directing the drive component to supply a rotational force comprises directing during a portion of the startup sequence for the gas turbine. 18. The method of claim 11, wherein directing the discharge of gas and directing the adjustment of the fuel flow shifts a rotating stall window associated with the compressor component. 19. The method of claim 11, further comprising: altering, by the one or more computing devices, an acceleration schedule associated with the startup of the gas turbine. 20. The method of claim 11, wherein directing the drive component comprises directing one of (i) a motor or (ii) a generator that receives power via a load commutated inverter.
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이 특허에 인용된 특허 (6)
Flatman, Richard J; Freeman, Christopher, Cycle gas turbine engine.
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