[특허]Method for operating a gas turbine plant and gas turbine plant for implementing the method

ANSALDO ENERGIA IP UK LIMITED

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특허 상세정보

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Method for operating a gas turbine plant and gas turbine plant for implementing the method

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/18 F01D-015/12 F02C-006/08 F02C-009/18
출원번호	US-0589494 (2012-08-20)
등록번호	US-9752504 (2017-09-05)
우선권정보	EP-11178309 (2011-08-22)
발명자 / 주소	Arias Chao, Manuel Wippel, Bernhard Balmer, Christian Jakoby, Ralf
출원인 / 주소	ANSALDO ENERGIA IP UK LIMITED
대리인 / 주소	Buchanan Ingersoll & Rooney PC
인용정보	피인용 횟수 : 0 인용 특허 : 11

초록
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A method is provided for operating a gas turbine plant including a compressor, which on an inlet side inducts intake air and compresses it, providing compressor exit air on a discharge side. The plant also includes a combustion chamber where fuel is combusted, using compressor exit air, forming a hot gas; and a turbine, where the hot gas is expanded, performing work. The method includes extracting compressed air from the compressor, directing it as cooling air flow into the combustion chamber and/or into the turbine for cooling thermally loaded components. The method also includes controlling at least one cooling air flow, for achieving specific operating targets, using a control element depending on an operating target. A gas turbine plant is also provided having at least one control element for cooling air flow control, and a gas turbine controller which controls the gas turbine plant based on selectable control parameter sets.

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1. A method for operating a gas turbine plant, comprising a compressor, which on an inlet side inducts intake air through variable inlet guide vanes and compresses it for providing compressor exit air on a discharge side, a combustion chamber, in which a fuel is combusted, using the compressor exit air, forming a hot gas, and a turbine, in which the hot gas is expanded, performing work, the method comprising: closing the variable inlet guide vanes to a minimum position during a low partial load operation;extracting compressed air from the compressor and directing the compressed air as cooling air flow into the combustion chamber and/or into the turbine for cooling thermally loaded components; andcontrolling an intermediate-pressure cooling air flow and/or a low-pressure cooling air flow during the low partial load operation for cooling thermally loaded components in the combustion chamber and/or in the turbine as a function of the turbine exhaust temperature to maintain turbine exhaust temperature above a turbine exhaust temperature (TAT) limit and as a function of inlet conditions into a heat recovery boiler. 2. The method as claimed in claim 1, wherein the cooling air flow for cooling thermally loaded components of the combustion chamber and/or of the turbine is also controlled as a function of the compressor exit pressure. 3. The method as claimed in claim 2, wherein at low ambient temperature the cooling air flow for cooling thermally loaded components of the combustion chamber and/or of the turbine is increased in order to reduce the compressor exit pressure. 4. The method as claimed in claim 1, wherein at low partial load the intermediate-pressure cooling air flow and/or the low-pressure cooling air flow for cooling thermally loaded components of the combustion chamber and/or of the turbine is reduced as a function of the turbine exhaust temperature (TAT) in order to keep the turbine exhaust temperature (TAT) constant. 5. The method as claimed in claim 4, wherein regardless of the turbine exhaust temperature (TAT) the intermediate-pressure cooling air flow and/or the low-pressure cooling air flow is not reduced below a minimum flow. 6. The method as claimed in claim 1, wherein regardless of the turbine exhaust temperature (TAT) the intermediate-pressure cooling air flow and/or the low-pressure cooling air flow is not reduced below a minimum flow. 7. The method as claimed in claim 1, wherein a recooling temperature of a recooler, in which the cooling air flow is recooled, is controlled in dependence upon a cooling air flow. 8. The method as claimed in claim 1, wherein the turbine exhaust temperature (TAT) is kept above a turbine exhaust temperature limit during a partial load operation at less than 40% of full load. 9. The method as claimed in claim 8, wherein the turbine exhaust temperature (TAT) is kept above a turbine exhaust temperature limit during a partial load operation at less than 25% of full load. 10. The method as claimed in claim 1, wherein the cooling air consumption during a partial load operation is reduced relative to cooling air consumption at full load for maintaining the turbine exhaust temperature (TAT) above the turbine exhaust temperature (TAT) limit. 11. The method as claimed in claim 1, wherein the extracted compressed air is directed into the combustion chamber and the turbine, and wherein a gas turbine controller is configured to control the intermediate-pressure cooling air flow and/or the low pressure cooling air flow for cooling thermally loaded components in the combustion chamber and in the turbine as a function of the turbine exhaust temperature (TAT) in order to keep the turbine exhaust temperature (TAT) above the turbine exhaust temperature (TAT) limit. 12. A gas turbine plant comprising a compressor, which on an inlet side inducts intake air through variable inlet guide vanes and compresses it for providing compressor exit air on a discharge side, a combustion chamber, in which a fuel is combusted, using the compressor exit air, forming hot gas, a turbine, in which the hot gas is expanded, performing work, wherein for cooling thermally loaded components of the combustion chamber and/or of the turbine a cooling air flow is directed from the compressor and/or from the exit of the compressor to the thermally loaded components, and at least one control element for controlling the cooling air flow, and a gas turbine controller, in which the control parameters for realizing a conventional operating concept are stored, and at least one additional set of control parameters, which is selected by an operator for realizing a specific operating concept, is stored in the gas turbine controller; wherein the gas turbine controller is configured to close the variable inlet guide vanes during a low partial load operation to a minimum position and to control an intermediate-pressure cooling air flow and/or a low pressure cooling air flow during the low partial load operation for cooling thermally loaded components in the combustion chamber and/or in the turbine as a function of the turbine exhaust temperature (TAT) in order to keep the turbine exhaust temperature (TAT) above a turbine exhaust temperature (TAT) limit and as a function of inlet conditions into a heat recovery boiler. 13. The gas turbine plant as claimed in claim 12, wherein at least one control element has a minimum opening which ensures a minimum cooling air flow to the thermally loaded components. 14. The gas turbine plant as claimed in claim 13, wherein at least one thermally loaded component comprises cooling air openings having a throughflow capacity which is at least 30% greater than a throughflow capacity which is required for achieving a design service life at a design point at full load. 15. The gas turbine plant as claimed in claim 12, wherein at least one thermally loaded component comprises cooling air openings having a throughflow capacity which is at least 30% greater than a throughflow capacity which is required for achieving a design service life at a design point at full load.

이 특허에 인용된 특허 (11)

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Method for operating a gas turbine plant and gas turbine plant for implementing the method

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Method for operating a gas turbine plant and gas turbine plant for implementing the method

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이 특허에 인용된 특허 (11)

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