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Kafe 바로가기국가/구분 | United States(US) Patent 등록 |
---|---|
국제특허분류(IPC7판) |
|
출원번호 | US-0067714 (2013-10-30) |
등록번호 | US-9631815 (2017-04-25) |
발명자 / 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 | 피인용 횟수 : 4 인용 특허 : 550 |
A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow distributor configured
A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow distributor configured to distribute at least one of an exhaust flow, an oxidant flow, an oxidant-exhaust mixture, or any combination thereof circumferentially around the head end chamber.
1. A system, comprising: a turbine combustor, comprising: a head end portion having a head end chamber;a combustion portion having a combustion chamber disposed downstream from the head end chamber;a cap disposed between the head end chamber and the combustion chamber; anda flow distributor comprisi
1. A system, comprising: a turbine combustor, comprising: a head end portion having a head end chamber;a combustion portion having a combustion chamber disposed downstream from the head end chamber;a cap disposed between the head end chamber and the combustion chamber; anda flow distributor comprising a plurality of flow distributor portions spaced circumferentially around the head end portion, and including a first flow distributor portion and a second flow distributor portion, wherein each flow distributor portion of the plurality of flow distributor portions is configured to receive an oxidant flow from an oxidant source and to route the oxidant flow axially along the head end portion; wherein the first flow distributor portion comprises a first exhaust gas flow path configured to receive a first compressed exhaust gas flow and to route the first compressed exhaust gas flow radially inward to a cooling region adjacent the cap; andwherein the second flow distributor portion comprises a second exhaust gas flow path configured to receive a second compressed exhaust gas flow and to route the second compressed exhaust gas flow radially outward to extract the second compressed exhaust gas flow from the turbine combustor. 2. The system of claim 1, wherein the first flow distributor portion comprises a first arcuate portion of the head end chamber, and the second flow distributor portion comprises a second arcuate portion of the head end chamber. 3. The system of claim 1, wherein the first and second flow distributor portions are circumferentially offset from one another. 4. The system of claim 1, wherein the first flow distributor portion comprises a plurality of first radial inserts, and the second flow distributor portion comprises a plurality of second radial inserts. 5. The system of claim 1, wherein the first flow distributor portion comprises a cooling gas flow path configured to convey an oxidant-exhaust mixture radially to the cooling region adjacent the cap and an oxidant-exhaust mixture path configured to convey the oxidant-exhaust mixture axially from a mixing region upstream of the plurality of flow distributor portions. 6. The system of claim 1, wherein the turbine combustor comprises an exhaust extraction port configured to extract a third compressed exhaust gas flow from the turbine combustor. 7. The system of claim 1, wherein the turbine combustor comprises an oxidant intake port configured to supply the oxidant flow to the turbine combustor. 8. The system of claim 1, comprising a gas turbine engine having the turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine, wherein the exhaust gas compressor is configured to compress and route an exhaust gas to the turbine combustor. 9. The system of claim 8, comprising an exhaust gas extraction system coupled to the gas turbine engine, and a hydrocarbon production system coupled to the exhaust gas extraction system. 10. The system of claim 8, wherein the gas turbine engine is a stoichiometric exhaust gas recirculation (SEGR) gas turbine engine. 11. A system, comprising: an oxidant compressor; anda gas turbine engine, comprising: a combustor section having a turbine combustor, wherein the turbine combustor comprises a cap disposed between a head end chamber and a combustion chamber;a turbine driven by combustion products from the turbine combustor;an exhaust gas compressor driven by the turbine, wherein the exhaust gas compressor is configured to compress and route an exhaust flow to the turbine combustor, and the oxidant compressor is configured to compress and route an oxidant flow to the turbine combustor;an exhaust extraction port coupled to the combustor section; anda flow distributor comprising a plurality of flow distributor portions spaced circumferentially around the head end chamber, and including a first flow distributor portion and a second flow distributor portion, wherein each flow distributor portion of the plurality of flow distributor portions is configured to receive the oxidant flow from the oxidant compressor and to route the oxidant flow axially along the head end chamber; wherein the first flow distributor portion comprises a first exhaust gas flow path configured to receive a first portion of the exhaust flow from the exhaust gas compressor and to route the first portion of the exhaust flow radially inward to a cooling region adjacent the cap; andwherein the second flow distributor portion comprises a second exhaust gas flow path configured to receive a second portion of the exhaust flow from the exhaust gas compressor and to route the second portion of the exhaust flow radially outward to extract the second portion of the exhaust flow from the turbine combustor. 12. The system of claim 11, wherein the exhaust extraction port is coupled to a casing disposed about the turbine combustor upstream of the flow distributor, coupled to the flow distributor, or any combination thereof. 13. The system of claim 11, wherein the turbine combustor comprises an oxidant intake port configured to supply the oxidant flow to the turbine combustor. 14. The system of claim 11, comprising a mixing region configured to mix the exhaust flow with the oxidant flow to provide an oxidant-exhaust mixture. 15. The system of claim 14, wherein the mixing region is disposed either upstream or downstream of the plurality of flow distributor portions. 16. A method, comprising: extracting an exhaust flow of an exhaust gas at a combustion section of a gas turbine engine and directing the exhaust flow toward a flow distributor, wherein the flow distributor comprises a plurality of flow distributor portions spaced circumferentially around the head end portion, and including a first flow distributor portion and a second flow distributor portion;routing a first portion of the exhaust flow through a first exhaust gas flow path of the first flow distributor portion radially inward to a cooling region adjacent a cap of the head end portion, wherein the cap is disposed between a head end region and a combustion region;routing a second portion of the exhaust flow through a second exhaust gas flow path of the second flow distributor portion radially outward to extract the second portion of the exhaust flow from the turbine combustor; androuting an oxidant flow through each of the flow distributor portions axially along the head end portion.
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