Method and system for gas turbine power augmentation using steam injection
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-003/30
F02C-007/143
G05D-007/06
출원번호
US-0064815
(2013-10-28)
등록번호
US-9732672
(2017-08-15)
발명자
/ 주소
Ewens, David Spencer
Mullen, Michael Corey
Meshram, Bhushan
출원인 / 주소
General Electric Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A method of augmenting power output by a gas turbine engine includes channeling fuel into the gas turbine engine at a predetermined fuel flow rate to generate a first power output. Steam is then injected into the gas turbine engine at a first steam flow rate, and a firing temperature bias is determi
A method of augmenting power output by a gas turbine engine includes channeling fuel into the gas turbine engine at a predetermined fuel flow rate to generate a first power output. Steam is then injected into the gas turbine engine at a first steam flow rate, and a firing temperature bias is determined based at least on the first steam flow rate. The predetermined fuel flow rate is then adjusted based on the determined firing temperature bias such that the gas turbine engine generates a second power output greater than the first power output.
대표청구항▼
1. A method of augmenting power output by a gas turbine engine using a computing device including at least one processor, said method comprising: channeling fuel into the gas turbine engine at a first fuel flow rate corresponding to a predetermined firing temperature limit to generate a first power
1. A method of augmenting power output by a gas turbine engine using a computing device including at least one processor, said method comprising: channeling fuel into the gas turbine engine at a first fuel flow rate corresponding to a predetermined firing temperature limit to generate a first power output, wherein firing temperature is a temperature of combustion gases located at an inlet to a turbine of the gas turbine engine;determining a first steam flow rate;injecting steam into the gas turbine engine at the first steam flow rate;calculating a firing temperature bias based on the first steam flow rate;calculating a suppressed firing temperature limit based on the predetermined firing temperature limit and the firing temperature bias; andchanneling fuel into the gas turbine engine at a second fuel flow rate corresponding to the suppressed firing temperature limit to generate a second power output greater than the first power output. 2. The method in accordance with claim 1 further comprising calculating a corrected steam flow rate based at least on the first steam flow rate. 3. The method in accordance with claim 2, wherein calculating a firing temperature bias further comprises calculating the firing temperature bias based on the calculated corrected steam flow rate. 4. The method in accordance with claim 2 further comprising measuring a temperature of air at a compressor inlet, wherein the corrected steam flow rate is based on the measured compressor inlet air temperature and the first steam flow rate. 5. The method in accordance with claim 1 further comprising measuring a mass flow rate of air within the gas turbine engine, wherein the first steam flow rate is based on the measured mass flow rate. 6. The method in accordance with claim 1, wherein channeling fuel into the gas turbine engine at a second fuel flow rate corresponding to the suppressed firing temperature limit reduces a firing temperature of the gas turbine engine from a first temperature at the first power output to a second temperature at the second power output. 7. A non-transitory computer-readable storage medium having computer-executable instructions embodied thereon, wherein when executed by a computing device having at least one processor, the computer-executable instructions cause the computing device to: operate a fuel delivery system to channel fuel into a gas turbine engine at a first fuel flow rate corresponding to a predetermined firing temperature limit to generate a first power output, wherein firing temperature is a temperature of combustion gases located at an inlet to a turbine of the gas turbine engine;receive a first steam flow rate;operate a steam injection system to inject steam into the gas turbine engine at the first steam flow rate;calculate a firing temperature bias based on the first steam flow rate;calculate a suppressed firing temperature limit based on the predetermined firing temperature limit and the firing temperature bias; andoperate the fuel delivery system to channel fuel into the gas turbine engine at a second fuel flow rate corresponding to the suppressed firing temperature limit to generate a second power output greater than the first power output. 8. The non-transitory computer-readable storage medium in accordance with claim 7, wherein when executed by the at least one processor, the computer-executable instructions further cause the at least one processor to calculate a corrected steam flow rate based on at least the first steam flow rate. 9. The non-transitory computer-readable storage medium in accordance with claim 8, wherein when executed by the at least one processor, the computer-executable instructions further cause the at least one processor to calculate the firing temperature bias based further on the calculated corrected steam flow rate. 10. The non-transitory computer-readable storage medium in accordance with claim 7, wherein when executed by the at least one processor, the computer-executable instructions further cause the at least one processor to operate the fuel delivery system to channel fuel into the gas turbine engine at the second fuel flow rate such that the firing temperature bias reduces a firing temperature of the gas turbine engine from a first temperature at the first power output to a second temperature at the second power output. 11. The non-transitory computer-readable storage medium in accordance with claim 7, wherein when executed by the at least one processor, the computer-executable instructions further cause the at least one processor to operate the fuel delivery system to channel fuel into the gas turbine engine at the first fuel flow rate to prevent exceeding a predetermined firing temperature limit when the gas turbine engine is operating at the first power output. 12. The non-transitory computer-readable storage medium in accordance with claim 7, wherein when executed by the at least one processor, the computer-executable instructions further cause the at least one processor to operate the steam injection system to inject steam into the gas turbine engine at the first steam flow rate based on a total mass flow rate of air through the gas turbine engine. 13. The non-transitory computer-readable storage medium in accordance with claim 7, wherein when executed by the at least one processor, the computer-executable instructions further cause the at least one processor to simultaneously increase a gas turbine engine power output while decreasing a gas turbine engine firing temperature. 14. A control system for augmenting power output by a gas turbine engine, said control system comprising; a plurality of sensors configured to measure various gas turbine engine operating parameters;a controller in communication with said plurality of sensors, said controller comprising a memory storage device and a processor in communication with said memory storage device, said processor configured to: receive the measured gas turbine engine operating parameters from the plurality of sensors;operate a fuel delivery system to channel fuel into the gas turbine engine at a first fuel flow rate corresponding to a predetermined firing temperature limit to generate a first power output, wherein firing temperature is a temperature of combustion gases located at an inlet to a turbine of the gas turbine engine;receive a first steam flow rate;operate a steam injection system to inject steam into the gas turbine engine at the first steam flow rate;calculate a firing temperature bias based on the first steam flow rate and at least one of the measured gas turbine operating parameters;calculate a suppressed firing temperature limit based on the predetermined firing temperature limit and the firing temperature bias; andoperate the fuel delivery system to channel fuel into the gas turbine engine at a second fuel flow rate corresponding to the suppressed firing temperature limit to generate a second power output greater than the first power output. 15. The control system in accordance with claim 14, wherein the processor is further configured to calculate a corrected steam flow rate based on the first steam flow rate and at least one of the measured gas turbine operating parameters. 16. The control system in accordance with claim 15, wherein the plurality of sensors includes a temperature sensor configured to measure a temperature of air at a compressor inlet, wherein the corrected steam flow rate is based on the measured compressor inlet air temperature and the first steam flow rate. 17. The control system in accordance with claim 15, wherein the processor is further configured to calculate the firing temperature bias based on the calculated corrected steam flow rate. 18. The control system in accordance with claim 14, wherein the plurality of sensors includes a mass flow sensor configured to measure a mass flow rate of air within the gas turbine engine, wherein the first steam flow rate is based on the measured mass flow rate. 19. The control system in accordance with claim 14, wherein the processor is further configured to operate the fuel delivery system to channel fuel into the gas turbine engine at the second fuel flow rate such that a first firing temperature of the gas turbine engine at the first power output is reduced to a second firing temperature at the second power output. 20. The control system in accordance with claim 14, wherein the processor is further configured to operate the fuel delivery system to channel fuel into the gas turbine engine at the first fuel flow rate to prevent exceeding a predetermined firing temperature limit when the gas turbine engine is operating at the first power output.
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이 특허에 인용된 특허 (4)
Jatila Ranasinghe ; Walter Phillip Jones, Gas turbine power augmentation injection system and related method.
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