최소 단어 이상 선택하여야 합니다.
최대 10 단어까지만 선택 가능합니다.
다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
NTIS 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
DataON 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
Edison 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
Kafe 바로가기국가/구분 | United States(US) Patent 등록 |
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국제특허분류(IPC7판) |
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출원번호 | US-0067844 (2013-10-30) |
등록번호 | US-9708977 (2017-07-18) |
발명자 / 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
|
인용정보 | 피인용 횟수 : 0 인용 특허 : 531 |
A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path, at least one main combustor disposed upstream from the turbine, wherein the at least one main
A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path, at least one main combustor disposed upstream from the turbine, wherein the at least one main combustor is configured to combust a fuel with a first oxidant and an exhaust gas to generate the combustion products, at least one reheat combustor disposed in or between turbine stages of the turbine, wherein the at least one reheat combustor is configured to reheat the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products, and an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path.
1. A system, comprising: a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path;at least one main combustor disposed upstream from the turbine, wherein the at least on
1. A system, comprising: a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path;at least one main combustor disposed upstream from the turbine, wherein the at least one main combustor is configured to combust a fuel with a first oxidant and an exhaust gas in a fuel-rich mode to generate the combustion products;at least one reheat combustor disposed in or between turbine stages of the turbine, wherein the at least one reheat combustor is configured to reheat the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products, wherein the at least one reheat combustor comprises a first reheat combustor having a first oxidant flow path through a first turbine nozzle of a first turbine stage of the plurality of turbine stages, the first turbine stage comprises a first set of rotary turbine blades downstream of the first turbine nozzle, the first oxidant flow path is configured to supply the second oxidant into the exhaust flow path, and the first reheat combustor comprises a first flame holder disposed downstream of the first turbine nozzle and upstream of the first set of rotary turbine blades of the first turbine stage; andan exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path. 2. The system of claim 1, comprising an oxidant compression system configured to compress and supply the first oxidant to the at least one main combustor, wherein the oxidant compression system is configured to compress and supply the second oxidant to the at least one reheat combustor. 3. The system of claim 1, wherein the first oxidant flow path is configured to supply the second oxidant into the exhaust flow path directly in the first turbine stage. 4. The system of claim 1, wherein the first oxidant flow path is configured to route the second oxidant through an additional structure after passing through the first turbine nozzle. 5. The system of claim 4, wherein the first oxidant flow path is configured to route the second oxidant through the additional structure upstream of the first turbine nozzle after passing through the first turbine nozzle. 6. The system of claim 5, wherein the additional structure comprises an additional turbine nozzle, an additional set of rotary turbine blades, or a combination thereof. 7. The system of claim 1, wherein the first oxidant flow path comprises a first plurality of openings disposed at a first trailing end portion of the first turbine nozzle. 8. The system of claim 1, wherein the at least one reheat combustor comprises a second reheat combustor having a second oxidant flow path through a second turbine nozzle of a second turbine stage of the plurality of turbine stages, wherein the second turbine stage comprises a second set of rotary turbine blades downstream of the second turbine nozzle, the second turbine stage is downstream of the first turbine stage, and the second oxidant flow path is configured to supply the second oxidant into the exhaust flow path. 9. The system of claim 1, comprising a gas turbine engine having the turbine, the at least one main combustor, the at least one reheat combustor, the exhaust gas compressor, and an exhaust gas recirculation system configured to recirculate the exhaust gas along the exhaust recirculation path from the turbine to the at least one main combustor, wherein the gas turbine engine is a stoichiometric exhaust gas recirculation (SEGR) gas turbine engine. 10. A method, comprising: driving a turbine with combustion products flowing along an exhaust flow path through a plurality of turbine stages;combusting a fuel with a first oxidant and an exhaust gas in a fuel-rich mode to generate the combustion products in at least one main combustor disposed upstream from the turbine;reheating the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products via at least one reheat combustor disposed in or between turbine stages of the turbine;compressing and routing the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path via an exhaust gas compressor;flowing the second oxidant along an oxidant flow path from a first component to a second component in an upstream direction along the exhaust flow path, wherein the first component comprises at least one turbine nozzle or at least one turbine blade, and the second component comprises the at least one turbine nozzle or the at least one turbine blade. 11. The method of claim 10, comprising holding a reheat flame with a flame holder of the at least one reheat combustor in or between the turbine stages. 12. The method of claim 10, comprising discharging the second oxidant from the oxidant flow path into the exhaust flow path through a plurality of openings, wherein the plurality of openings is disposed in the at least one turbine nozzle, the at least one turbine blade, or a combination thereof. 13. A system, comprising: a main combustor configured to combust a first fuel flow with a first oxidant flow in a fuel-rich mode to produce combustion products and an unburned fuel flow;a turbine section configured to receive the combustion products and the unburned fuel flow, comprising: a first turbine stage comprising a first turbine nozzle and a first set of rotary turbine blades downstream of the first turbine nozzle;a first reheat combustor positioned within the first turbine stage, comprising a first flame holding mechanism, wherein a first oxidant flow path is configured to route a second oxidant flow through an additional structure of the turbine section upstream of the first turbine nozzle after passing through the first turbine nozzle, and the first oxidant flow path is configured to supply the second oxidant into the combustion products and unburned fuel flow;a second turbine stage positioned downstream of the first reheat combustor; anda second reheat combustor positioned downstream of the second turbine stage, comprising a second flame holding mechanism. 14. The system of claim 13, wherein the second turbine stage comprises a second turbine nozzle configured to flow a third oxidant flow into the turbine section and toward the second flame holding mechanism. 15. The system of claim 14, wherein the second turbine stage comprises a second set of rotary turbine blades disposed between the second turbine nozzle and the second flame holding mechanism. 16. The system of claim 13, wherein the second turbine stage comprises a second set of rotary turbine blades configured to flow a third oxidant flow into the turbine section and toward the second flame holding mechanism. 17. The system of claim 13, comprising a controller configured to regulate flow of the first fuel flow and the first oxidant flow into the main combustor such that the main combustor operates in the fuel-rich mode.
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