[특허]Control method for cooling a turbine stage in a gas turbine

Ansaldo Energia S.p.A.

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특허 상세정보

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Control method for cooling a turbine stage in a gas turbine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-006/08 F02C-007/12 F02C-007/18 F02C-009/18
미국특허분류(USC)	060/782; 060/806
출원번호	US-0253316 (2011-10-05)
등록번호	US-8881532 (2014-11-11)
우선권정보	IT-TO2010A0824 (2010-10-06)
발명자 / 주소	Bozzi, Luca Mantero, Marco Bonzani, Federico
출원인 / 주소	Ansaldo Energia S.p.A.
대리인 / 주소	Greenblum & Bernstein, P.L.C.
인용정보	피인용 횟수 : 0 인용 특허 : 5

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A control method for cooling a turbine stage of a gas turbine, whereby cooling air is bled from combustion air flowing in a compressor of the gas turbine, and is fed to a cooling circuit staring from a stator of the turbine stage; and cooling airflow is adjusted as a function of the pressure at the inlet of the cooling circuit, and as a function of the combustion air pressure at the exhaust of the compressor; more specifically, there is a feedback control setting a setpoint, which is predetermined as a function of the power output of the turbine to reduc...

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1. A control method for cooling a turbine stage of a gas turbine, the method comprising: bleeding cooling air from combustion air flowing in a compressor of said gas turbine, and feeding the bled cooling air to a cooling circuit starting from a stator of said turbine stage; andregulating cooling airflow to said cooling circuit as a function of the pressure (POair) at an inlet of said cooling circuit,wherein the cooling airflow is adjusted as a function of a combustion air pressure (Pcomp) of said compressor, andwherein the cooling airflow is adjusted by feedback-controlling an opening of a valve as a function of a cooling air temperature (Tairrot) at an outlet of said stator. 2. The method as claimed in claim 1, wherein the cooling airflow is adjusted as a function of the combustion air pressure (Pcomp) at an exhaust of said compressor. 3. The method as claimed in claim 1, wherein the cooling airflow is adjusted as a function of a ratio between the pressure (POair) at the inlet of said cooling circuit, and the combustion air pressure (Pcomp). 4. The method as claimed in claim 3, wherein the cooling airflow is adjusted by feedback-controlling the opening of the valve to achieve a predetermined target of said ratio. 5. The method as claimed in claim 4, wherein the predetermined target is a function of a parameter defined by a power output (P) of the turbine, or by a temperature (Tgas) of burnt gases at an exhaust of the turbine. 6. The method as claimed in claim 5, wherein said target is predetermined by setting a reference signal (S) to: a first value (REF) in a first range of said parameter;a second value (REF1), higher than the first value (REF), in a second range, following the first range, of said parameter; anda third value (REF2), lower than the first value (REF), in a third range, following the second range, of said parameter. 7. The method as claimed in claim 6, wherein a difference between the second and first value (REF1-REF) is greater than a difference between the first and third value (REF-REF2). 8. The method as claimed in claim 6, wherein said reference signal (S) equals the first value (REF) for a power output (P) equal to a nominal power output of the turbine. 9. The method as claimed in claim 6, wherein said target is predetermined by correcting said reference signal (S) as a function of the cooling air temperature (Tairrot) at the outlet of said stator. 10. The method as claimed in claim 9, wherein said correction is made as a function of a metal temperature of blades in said turbine stage, and said metal temperature being estimated as a function of the cooling air temperature (Tairrot) at the outlet of said stator, the gas temperature (Tgas) at the exhaust of the turbine, and a cooling air temperature (Tair) at the inlet of said cooling circuit. 11. The method as claimed in claim 9, wherein an amount of said correction is determined as a function of the power output of said turbine. 12. The method as claimed in claim 9, wherein the cooling air temperature (Tairrot) is measured in an inner ring of said stator. 13. The method as claimed in claim 1, wherein said cooling circuit comprises a first and second portion arranged in succession and formed in said stator and in a rotor of said turbine stage respectively. 14. The method as claimed in claim 1, wherein the pressure (POair) at the inlet of said cooling circuit is measured in an annular conduit formed in an outer annular structure of said stator. 15. A control method for cooling a turbine stage of a gas turbine, the method comprising: bleeding cooling air from combustion air flowing in a compressor of said gas turbine, and feeding the bled cooling air to a cooling circuit starting from a stator of said turbine stage; andregulating cooling airflow to said cooling circuit as a function of the pressure (POair) at an inlet of said cooling circuit,wherein the cooling airflow is adjusted as a function of a combustion air pressure (Pcomp) of said compressor,wherein the cooling airflow is adjusted as a function of a ratio between the pressure (POair) at the inlet of said cooling circuit, and the combustion air pressure (Pcomp),wherein the cooling airflow is adjusted by feedback-controlling the opening of the valve to achieve a predetermined target of said ratio,wherein the predetermined target is a function of a parameter defined by a power output (P) of the turbine, or by a temperature (Tgas) of burnt gases at an exhaust of the turbine, andwherein said target is predetermined by setting a reference signal (S) to: a first value (REF) in a first range of said parameter;a second value (REF1), higher than the first value (REF), in a second range, following the first range, of said parameter; anda third value (REF2), lower than the first value (REF), in a third range, following the second range, of said parameter. 16. The method as claimed in claim 15, wherein said correction is made as a function of a metal temperature of blades in said turbine stage, and said metal temperature being estimated as a function of the cooling air temperature (Tairrot) at the outlet of said stator, the gas temperature (Tgas) at the exhaust of the turbine, and a cooling air temperature (Tair) at the inlet of said cooling circuit. 17. The method as claimed in claim 15, wherein an amount of said correction is determined as a function of the power output of said turbine. 18. The method as claimed in claim 15, wherein the cooling air temperature (Tairrot) is measured in an inner ring of said stator. 19. A control method for cooling a turbine stage of a gas turbine, the method comprising: bleeding cooling air from combustion air flowing in a compressor of said gas turbine, and feeding the bled cooling air to a cooling circuit starting from a stator of said turbine stage; andregulating cooling airflow to said cooling circuit as a function of the pressure (POair) at an inlet of said cooling circuit,wherein the cooling airflow is adjusted as a function of a combustion air pressure (Pcomp) of said compressor, andwherein said cooling circuit comprises a first and second portion arranged in succession and formed in said stator and in a rotor of said turbine stage respectively. 20. A control method for cooling a turbine stage of a gas turbine, the method comprising: bleeding cooling air from combustion air flowing in a compressor of said gas turbine, and feeding the bled cooling air to a cooling circuit starting from a stator of said turbine stage; andregulating cooling airflow to said cooling circuit as a function of the pressure (POair) at an inlet of said cooling circuit,wherein the cooling airflow is adjusted as a function of a combustion air pressure (Pcomp) of said compressor, andwherein the pressure (POair) at the inlet of said cooling circuit is measured in an annular conduit formed in an outer annular structure of said stator.

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Control method for cooling a turbine stage in a gas turbine

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Control method for cooling a turbine stage in a gas turbine

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