[특허]Turbine to operate at part-load

General Electric Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Turbine to operate at part-load

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-009/18 F01D-005/18 F01D-009/06 F02C-007/14
출원번호	US-0343269 (2012-01-04)
등록번호	US-9169782 (2015-10-27)
발명자 / 주소	Subramaniyan, Moorthi Garg, Umesh John, Joshy Valliappan, Lakshmanan
출원인 / 주소	General Electric Company
대리인 / 주소	Cusick, Ernest G.
인용정보	피인용 횟수 : 1 인용 특허 : 6

초록

A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section.

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1. A turbine to operate at part-load, comprising: a compressor to intake a fluid;a combustion chamber to heat the fluid from the compressor;a turbine section to rotate a shaft with the heated fluid from the combustion chamber, the turbine section comprising a plurality of nozzles and each nozzle having a nozzle opening defined by first and second airfoils, an inner airfoil support and an outer airfoil support, wherein a cavity extends between the outer and inner airfoil supports and circumferentially spans respective portions of the at least one of the first and second airfoils and the adjacent nozzle;a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor and transmitting the portion of the fluid to the turbine section; anda controller to determine whether a part-load operation is selected, and to open the bypass circuit when the part-load operation is selected,wherein when the controller determines that the part-load operation is selected, the controller determines a normal part-load fluid intake to the compressor, increases the part-load fluid intake to the compressor by a predetermined first percentage above the normal part-load fluid intake, and controls the bypass circuit to remove the portion of the fluid from the compressor such that a percentage of the portion of the fluid removed from the compressor relative to the increased part-load fluid intake is less than or equal to the predetermined first percentage. 2. The turbine of claim 1, wherein the compressor includes a fluid intake device, and the controller controls the fluid intake device to increase the part-load fluid intake. 3. The turbine of claim 1, wherein the controller increases the part-load fluid intake by 20% and controls the bypass circuit to remove 15% of the fluid from the compressor. 4. A turbine, comprising: a compressor to intake a fluid and to compress the fluid;a combustion chamber to heat the fluid from the compressor;a turbine section to rotate a shaft with the heated fluid from the combustion chamber, the turbine section comprising a plurality of nozzles and each nozzle having a nozzle opening defined by first and second airfoils, an inner airfoil support and an outer airfoil support; anda bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section,a cavity extends between the outer and inner airfoil supports and circumferentially spans respective portions of the at least one of the first and second airfoils and the adjacent nozzle. 5. The turbine of claim 4, wherein the bypass circuit includes at least one of a steam generator and a firing unit to heat the bypass flow. 6. The turbine of claim 4, wherein the turbine further includes an exhaust section, and the bypass circuit heats the bypass flow with a heated fluid from the exhaust section. 7. The turbine of claim 4, wherein the compressor includes at least eleven stages, and the bypass circuit removes the portion of the fluid from at least one of a third stage through an eleventh stage from among the at least eleven stages, where the at least eleven stages are numbered in order from an intake end of the compressor to a combustion chamber end of the compressor. 8. The turbine of claim 4, wherein the turbine section includes at least three stages numbered in ascending order from a combustion end of the turbine section to an output end of the turbine section, the at least three stages including a last stage adjacent to the output end of the turbine section, and the bypass circuit inserts the bypass flow to the last stage of the turbine section. 9. The turbine of claim 8, wherein each stage of the turbine section includes one of the plurality of nozzles to direct the heated fluid to buckets and the bypass circuit inserts the bypass flow through the outer airfoil support into the nozzle opening. 10. The turbine of claim 4, further comprising a cooling circuit to provide a purge flow to the turbine section, wherein a casing of the turbine section includes a purge flow inlet to receive the purge flow and a separate bypass flow inlet to receive the bypass flow. 11. A turbine, comprising: a compressor to intake a fluid and to compress the fluid;a combustion chamber to heat the fluid from the compressor;a turbine section to rotate a shaft with the heated fluid from the combustion chamber;a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section; anda cooling circuit to provide a purge flow to the turbine section,wherein a casing of the turbine section includes a purge flow inlet to receive the purge flow and a separate bypass flow inlet to receive the bypass flow,the turbine section includes a plurality of nozzles, each nozzle having a nozzle opening defined by first and second airfoils, an inner airfoil support, and an outer airfoil support,the cooling circuit inputs the purge flow into at least one of the first and second airfoils of at least one of the plurality of nozzles, andthe bypass circuit inserts the bypass flow into the nozzle opening of the at least one of the plurality of nozzles. 12. The turbine of claim 11, wherein the at least one of the first and second airfoils includes a cavity extending between the outer airfoil support and the inner airfoil support, and the purge flow inlet is connected to the cavity, and the outer airfoil support of the at least one of the plurality of nozzles includes an outlet to receive the bypass flow from the bypass flow inlet and to insert the bypass flow into the nozzle opening. 13. The turbine of claim 11, wherein the outer airfoil support includes a cavity having a divider to divide the cavity into two sections, and the purge flow inlet opens into one of the two sections and the bypass flow inlet opens into the other of the two sections. 14. The turbine of claim 13, wherein the divider includes an opening connecting the two sections. 15. The turbine of claim 10, wherein the turbine section includes a plurality of nozzles, each nozzle having a nozzle opening defined by first and second airfoils, an inner airfoil support, and an outer airfoil support, the cooling circuit inputs the purge flow into a purge flow cavity of the first airfoil, andthe bypass circuit inserts the bypass flow into a bypass flow cavity of the first airfoil. 16. The turbine of claim 15, wherein the first airfoil includes an opening to connect the bypass flow cavity to the nozzle opening. 17. A turbine section of a turbine, comprising: a casing;a rotor including a shaft and buckets extending radially from the shaft; andnozzles comprising a plurality of airfoils positioned between an outer airfoil support connected to the casing and an inner airfoil support adjacent to the shaft of the rotor to define a nozzle opening,each nozzle having a nozzle opening defined by first and second airfoils, an inner airfoil support and an outer airfoil support and a cavity extends between the outer and inner airfoil supports and circumferentially spans respective portions of the at least one of the first and second airfoils and the adjacent nozzle,wherein the casing includes a first inlet to receive a purge flow to cool at least the plurality of airfoils and a second inlet to receive a bypass flow to supply the bypass flow to the buckets of the rotor. 18. The turbine section of claim 17, wherein the turbine section includes a plurality of stages, each stage comprising an annular group of the nozzles and an adjacent annular group of the buckets, and the second inlet is located at a last stage of the plurality of stages. 19. A turbine section of a turbine, comprising: a casing;a rotor including a shaft and buckets extending radially from the shaft; andnozzles comprising a plurality of airfoils positioned between an outer airfoil support connected to the casing and an inner airfoil support adjacent to the shaft of the rotor to define a nozzle opening,wherein the casing includes a first inlet to receive a purge flow to cool at least the plurality of airfoils and a second inlet to receive a bypass flow to supply the bypass flow to the buckets of the rotor,at least one of the plurality of airfoils includes a purge flow cavity and a bypass flow cavity, the purge flow cavity having an inlet at one end and an outlet at an opposing end, the bypass flow cavity having an inlet at the one end and an outlet along a side of the at least one of the plurality of airfoils to transmit the bypass flow to the nozzle opening, andthe first inlet of the casing is connected to the inlet of the purge flow cavity and the second inlet of the casing is connected to the inlet of the bypass flow cavity. 20. The turbine section of claim 19, wherein the at least one of the plurality of airfoils includes at least one opening between the purge flow cavity and the bypass flow cavity.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 1

Subramaniyan, Moorthi; John, Joshy. Turbine flow modulation for part load performance. USP2017019534536.

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Turbine to operate at part-load

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Turbine to operate at part-load

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