System and method for augmenting gas turbine power output
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-006/16
F02C-003/04
F02C-006/08
출원번호
US-0859819
(2013-04-10)
등록번호
US-8984893
(2015-03-24)
발명자
/ 주소
Schroder, Mark Stewart
Wickert, Thomas Edward
Hadley, Mark Allan
출원인 / 주소
General Electric Company
대리인 / 주소
Dority & Manning, PA
인용정보
피인용 횟수 :
3인용 특허 :
9
초록▼
A system for augmenting gas turbine power output includes a compressed air supply, and a compressed air storage plenum in fluid communication with the compressed air supply. The compressed air storage plenum is configured to store a compressed air from the compressed air supply for later use. The sy
A system for augmenting gas turbine power output includes a compressed air supply, and a compressed air storage plenum in fluid communication with the compressed air supply. The compressed air storage plenum is configured to store a compressed air from the compressed air supply for later use. The system further includes an inlet plenum sealingly coupled to an inlet of the gas turbine. The inlet plenum is in fluid communication with the compressed air storage plenum so as to route the compressed air from the compressed air storage plenum into the inlet of the compressor during augmented operation of the gas turbine.
대표청구항▼
1. A system for enhancing performance of a gas turbine, the system comprising: a. a compressed air supply comprising a compressor of the gas turbine;b. a compressed air storage plenum in fluid communication with the compressed air supply, the compressed air storage plenum being configured to store a
1. A system for enhancing performance of a gas turbine, the system comprising: a. a compressed air supply comprising a compressor of the gas turbine;b. a compressed air storage plenum in fluid communication with the compressed air supply, the compressed air storage plenum being configured to store a compressed air from the compressed air supply;c. an inlet plenum sealingly coupled to an inlet of the compressor, the inlet plenum being in fluid communication with the compressed air storage plenum and the inlet of the compressor, wherein the inlet plenum is pressurized with the compressed air from the compressed air storage plenum during augmented mode of operation of the gas turbine; andd. a bleed air flow path that extends between one of a to or an exhaust gas section of the gas turbine and the compressed air storage plenum, wherein the bleed air flow path provides for fluid communication between the turbine or the exhaust gas section and the compressed air storage plenum. 2. The system as in claim 1, wherein the inlet plenum is sealed to allow for pressurization. 3. The system as in claim 1. wherein the compressed air storage plenum comprises at least one of an underground geologically formed cavern, a below ground pressure vessel or an above ground pressure vessel. 4. The system as in claim 1, further comprising an extraction air flow path defined between the compressed air supply and the compressed air storage plenum and an inlet pressurization flow path defined between the compressed air storage plenum and the inlet plenum. 5. The system as in claim 4, further comprising at least one flow conditioning device disposed within at least one of the extraction air flow path or the inlet pressurization flow path. 6. The system as in claim 1, wherein the inlet plenum is pressurized by the compressed air to a pressure that is greater than an ambient atmospheric, pressure. 7. The system as in claim 1, wherein the inlet plenum is pressurized to a pressure of at least 1.0 bar. 8. A gas turbine, comprising: a. an inlet plenum, a compressor downstream from the inlet plenum, a combustor downstream from the compressor, a turbine downstream from the combustor and an exhaust gas section downstream from the turbine, the compressor having an extraction port;b. a compressed air storage plenum in fluid communication with the compressor;c. an inlet pressurization flow path that provides for fluid communication between the compressed air storage plenum and the inlet plenum, wherein the inlet plenum is pressurized with compressed air from the compressed air storage plenum during augmentation mode of operation of the gas turbine;d. a first bleed air flow path defined between the compressor and the inlet plenum, wherein the bleed air flow path provides for fluid communication between the compressor and the inlet plenum; ande. a secondary bleed air flow path fluidly connected to the gas turbine at a location downstream from the compressor, wherein the secondary bleed air flow path provides for fluid communication into the compressed air storage plenum. 9. The gas turbine as in claim 8, wherein the compressed air storage plenum comprises at least one of a geologically formed compressed air storage cavern or a pressure vessel. 10. The gas turbine as in claim 8, further comprising an extraction air flow path defined between an extraction port of the compressor and the compressed air storage plenum to route a compressed air from the compressor to the compressed air storage plenum. 11. The gas turbine as in claim 8, further comprising an inlet pressurization flow path defined between the compressed air storage plenum and the inlet plenum to route a compressed air from the compressed air storage plenum to the inlet plenum. 12. The gas turbine as in claim 8, further comprising one or more secondary bleed air flow paths that provide for fluid communication of compressed air from at least one of the combustor, the turbine and the exhaust gas section, to the inlet plenum. 13. The gas turbine as in claim 12, further comprising at least one flow conditioning device disposed within at least one of the one or more secondary bleed air flow paths. 14. The gas turbine as in claim 8, further comprising one or more secondary bleed air flow paths that provide for fluid communication of compressed air between the compressed air storage plenum and at least one of the turbine and the exhaust gas section. 15. A method for operating a gas turbine, comprising a. compressing air within a compressor of the gas turbine to provide a flow of compressed air through the gas turbine;b. routing the compressed air from the vas turbine at a location that is defined downstream from the compressor via one or more bleed air flow paths that provide for fluid communication between the gas turbine and a compressed air storage plenum during a pressurization mode of operation of the gas turbine;c. routing the compressed air from the compressed air storage plenum to an inlet plenum disposed upstream from an inlet to the compressor;d. sealing one or more openings of the inlet plenum;e. pressurizing the inlet plenum with the compressed air from the compressed air storage plenum; andf. routing the compressed air from the pressurized inlet plenum into the inlet of the compressor during an augmentation mode of operation of the gas turbine. 16. The method as in claim 15, wherein the inlet plenum is pressurized to at least 1.0 bar. 17. The method as in claim 15, further comprising routing a portion of the compressed air directly from the compressor to the inlet plenum during the pressurization mode of operation. 18. The method as in claim 15, further comprising routing a portion of excess compressed air from a secondary bleed air flow path to at least one of the compressed air storage plenum or the inlet plenum during the pressurization mode of operation.
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이 특허에 인용된 특허 (9)
Nakhamkin Michael ; Potashnik Boris, Combustion turbine power plant operable at full power using supplemental compressed air.
Kelller-Sornig, Peter; Mazza, Edoardo; Seketa, Bozidar, Compressed air energy storage system having a standby warm keeping system including an electric air heater.
Nakhamkin Michael ; Potashnik Boris, Method of operating a combustion turbine power plant at full power at high ambient temperature or at low air density using supplemental compressed air.
Nakhamkin, Michael, Retrofit of simple cycle gas turbine for compressed air energy storage application having expander for additional power generation.
Brostmeyer, Joseph D; Memmen, Robert L, Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir.
Brostmeyer, Joseph D; Memmen, Robert L, Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir.
Brostmeyer, Joseph D; Memmen, Robert L, Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir.
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