IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0657132
(2007-01-24)
|
등록번호 |
US-7756626
(2010-08-02)
|
우선권정보 |
JP-2006-141092(2006-05-22) |
발명자
/ 주소 |
- Fujii, Kentaro
- Toyama, Kozo
|
출원인 / 주소 |
- Mitsubishi Heavy Industries, Ltd.
|
대리인 / 주소 |
Westerman, Hattori, Daniels & Adrian, LLP
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인용정보 |
피인용 횟수 :
10 인용 특허 :
2 |
초록
▼
A gas turbine output learning circuit is configured to compute a current combustion gas temperature TIT at an inlet of a gas turbine by linear interpolation by use of two characteristic curves A and B respectively representing relations between a pressure ratio and an exhaust gas temperature in the
A gas turbine output learning circuit is configured to compute a current combustion gas temperature TIT at an inlet of a gas turbine by linear interpolation by use of two characteristic curves A and B respectively representing relations between a pressure ratio and an exhaust gas temperature in the cases of the combustion gas temperature at the inlet of the gas turbine at 1400° C. and 1500° C., then to compute ideal MW corresponding to this combustion gas temperature TIT at the inlet of the gas turbine by linear interpolation according to 1400° C.MW and 1500° C.MW (temperature controlled MW), and then to correct the 1400° C.MW and the 1500° C.MW so as to match the ideal MW with a measured gas turbine output (a power generator output).
대표청구항
▼
What is claimed is: 1. A gas turbine output learning circuit for a gas turbine having a gas turbine body, a combustor, and a compressor, comprising: means for computing a first exhaust gas temperature corresponding to a measured pressure ratio according to a first characteristic curve representing
What is claimed is: 1. A gas turbine output learning circuit for a gas turbine having a gas turbine body, a combustor, and a compressor, comprising: means for computing a first exhaust gas temperature corresponding to a measured pressure ratio according to a first characteristic curve representing a relation between the pressure ratio of the compressor and an exhaust gas temperature of the gas turbine body when a combustion gas temperature at an inlet of the gas turbine is adjusted to a first combustion gas temperature at the inlet of the gas turbine; means for computing a second exhaust gas temperature corresponding to a measured pressure ratio according to a second characteristic curve representing a relation between the pressure ratio and the exhaust gas temperature when the combustion gas temperature at the inlet of the gas turbine is adjusted to a second combustion gas temperature at the inlet of the gas turbine, which is higher than the first combustion gas temperature at the inlet of the gas turbine; means for computing a third combustion gas temperature at the inlet of the gas turbine corresponding to the measured pressure ratio and a measured exhaust gas temperature by linear interpolation according to the first combustion gas temperature at the inlet of the gas turbine, the second combustion gas temperature at the inlet of the gas turbine, the first exhaust gas temperature, the second exhaust gas temperature, and the measured exhaust gas temperature; means for computing a third gas turbine output corresponding to the third combustion gas temperature at the inlet of the gas turbine by linear interpolation according to a first gas turbine output corresponding to the first combustion gas temperature at the inlet of the gas turbine and a second gas turbine output corresponding to the second combustion gas temperature at the inlet of the gas turbine which are computed by gas turbine output computing means, the first combustion gas temperature at the inlet of the gas turbine, the second combustion gas temperature at the inlet of the gas turbine, and the third combustion gas temperature at the inlet of the gas turbine; and means for correcting the first gas turbine output and the second gas turbine output which are used for computation of the third gas turbine output by comparing the third gas turbine output with a measured gas turbine output so as to match the third gas turbine output with the measured gas turbine output. 2. The gas turbine output learning circuit according to claim 1, wherein the means for correcting the first gas turbine output and the second gas turbine output is configured to correct the first gas turbine output and the second gas turbine output by calculating a correction coefficient while performing any of a proportional-integral operation and an integral operation of a deviation between the third gas turbine output and the measured gas turbine output and multiplying each of the first gas turbine output and the second gas turbine output by this correction coefficient. 3. The gas turbine output learning circuit according to claim 2, further comprising means for weighting the deviation between the third gas turbine output and the measured gas turbine output so as to increase a weighted coefficient used for multiplication of the deviation in response to an increase in a combustion load command value to render the combustion gas temperature at the inlet of the gas turbine computed by combustion load command value computing means dimensionless or means for weighting said deviation so as to increase the weighted coefficient used for multiplication of the deviation in response to an increase in the third combustion gas temperature at the inlet of the gas turbine. 4. A combustion control device for a gas turbine which is fitted to a gas turbine provided with a gas turbine body, a combustor having multiple types of fuel nozzles, a compressor installed with an inlet guide vane, and multiple fuel flow rate control valves for respectively controlling fuel supplies to the multiple types of the fuel nozzles, the combustion control device being configured to control the fuel supplies to the multiple types of the fuel nozzles by controlling apertures of the fuel flow rate control valves, the combustion control device comprising: gas turbine output computing means for computing a first gas turbine output corresponding to a first combustion gas temperature at an inlet of the gas turbine, a second gas turbine output corresponding to a second combustion gas temperature at the inlet of the gas turbine being higher than the first combustion gas temperature at the inlet of the gas turbine, and a fourth gas turbine output corresponding to a fourth combustion gas temperature at the inlet of the gas turbine being lower than the second combustion gas temperature at the inlet of the gas turbine according to an intake-air temperature of the compressor and an aperture of the inlet guide vane; and combustion load command computing means for computing a combustion load command value to render the combustion gas temperature at the inlet of the gas turbine dimensionless by linear interpolation according to the second gas turbine output, the fourth gas turbine output and a measured gas turbine output, wherein the combustion control device controls the fuel supplies to the multiple types of the fuel nozzles by determining ratios of fuels to be supplied respectively to the multiple types of the fuel nozzles according to the combustion load command value computed by the combustion load command computing means, and by controlling apertures of the fuel flow rate control valves according to the ratio of the fuels, and the combustion control device for a gas turbine comprises a gas turbine output learning circuit comprising: means for computing a first exhaust gas temperature corresponding to a measured pressure ratio according to a first characteristic curve representing a relation between the pressure ratio of the compressor and an exhaust gas temperature of the gas turbine body when a combustion gas temperature at an inlet of the gas turbine is adjusted to the first combustion gas temperature at the inlet of the gas turbine; means for computing a second exhaust gas temperature corresponding to a measured pressure ratio according to a second characteristic curve representing a relation between the pressure ratio and the exhaust gas temperature when the combustion gas temperature at the inlet of the gas turbine is adjusted to the second combustion gas temperature at the inlet of the gas turbine; means for computing a third combustion gas temperature at the inlet of the gas turbine corresponding to the measured pressure ratio and a measured exhaust gas temperature by linear interpolation according to the first combustion gas temperature at the inlet of the gas turbine, the second combustion gas temperature at the inlet of the gas turbine, the first exhaust gas temperature, the second exhaust gas temperature, and the measured exhaust gas temperature; means for computing a third gas turbine output corresponding to the third combustion gas temperature at the inlet of the gas turbine by linear interpolation according to the first gas turbine output corresponding to the first combustion gas temperature at the inlet of the gas turbine and the second gas turbine output corresponding to the second combustion gas temperature at the inlet of the gas turbine, which are computed by the gas turbine output computing means, the first combustion gas temperature at the inlet of the gas turbine, the second combustion gas temperature at the inlet of the gas turbine, and the third combustion gas temperature at the inlet of the gas turbine; and means for correcting the first gas turbine output and the second gas turbine output used for computation of the third gas turbine output so as to match the third gas turbine output with the measured gas turbine output by comparing the third gas turbine output with a measured gas turbine output and, wherein the second gas turbine output corrected by the gas turbine output learning circuit is used for computation of the combustion load command value by the combustion load command value computing means. 5. The combustion control device for a gas turbine according to claim 4, wherein the means for correcting the first gas turbine output and the second gas turbine output in the gas turbine output learning circuit is configured to correct the first gas turbine output and the second gas turbine output by calculating a correction coefficient while performing any of a proportional-integral operation and an integral operation of a deviation between the third gas turbine output and the measured gas turbine output and by multiplying each of the first gas turbine output and the second gas turbine output by this correction coefficient. 6. The combustion control device for a gas turbine according to claim 5, wherein the gas turbine output learning circuit comprises means for weighting a deviation between the third gas turbine output and the measured gas turbine output so as to increase a weighted coefficient used for multiplication of the deviation in response to an increase in a combustion load command value to render the combustion gas temperature at the inlet of the gas turbine computed by the combustion load command value computing means dimensionless or means for weighting said deviation so as to increase the weighted coefficient used for multiplication of the deviation in response to an increase in the third combustion gas temperature at the inlet of the gas turbine. 7. The combustion control device for a gas turbine according to claim 6, wherein the gas turbine comprises gas turbine bypassing means for bypassing compressed air to any of the combustor and the gas turbine body, and the gas turbine output computing means computes the first gas turbine output, the second gas turbine output, and the fourth gas turbine output according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, and a turbine bypass ratio equivalent to a ratio between a total amount of compressed air by the compressor and a turbine bypass flow rate by the gas turbine bypassing means. 8. The combustion control device for a gas turbine according to claim 6, wherein the gas turbine output computing means computes the first gas turbine output, the second gas turbine output, and the fourth gas turbine output according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, and an atmospheric pressure ratio equivalent to a ratio between the intake pressure of the compressor and a standard atmospheric pressure or according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, the turbine bypass ratio, and the atmospheric pressure ratio. 9. The combustion control device for a gas turbine according to claim 5, wherein the gas turbine comprises gas turbine bypassing means for bypassing compressed air to any of the combustor and the gas turbine body, and the gas turbine output computing means computes the first gas turbine output, the second gas turbine output, and the fourth gas turbine output according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, and a turbine bypass ratio equivalent to a ratio between a total amount of compressed air by the compressor and a turbine bypass flow rate by the gas turbine bypassing means. 10. The combustion control device for a gas turbine according to claim 5, wherein the gas turbine output computing means computes the first gas turbine output, the second gas turbine output, and the fourth gas turbine output according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, and an atmospheric pressure ratio equivalent to a ratio between the intake pressure of the compressor and a standard atmospheric pressure or according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, the turbine bypass ratio, and the atmospheric pressure ratio. 11. The combustion control device for a gas turbine according to claim 4, wherein the gas turbine comprises gas turbine bypassing means for bypassing compressed air to any of the combustor and the gas turbine body, and the gas turbine output computing means computes the first gas turbine output, the second gas turbine output, and the fourth gas turbine output according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, and a turbine bypass ratio equivalent to a ratio between a total amount of compressed air by the compressor and a turbine bypass flow rate by the gas turbine bypassing means. 12. The combustion control device for a gas turbine according to claim 11, wherein the gas turbine output computing means computes the first gas turbine output, the second gas turbine output, and the fourth gas turbine output according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, and an atmospheric pressure ratio equivalent to a ratio between the intake pressure of the compressor and a standard atmospheric pressure or according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, the turbine bypass ratio, and the atmospheric pressure ratio. 13. The combustion control device for a gas turbine according to claim 4, wherein the gas turbine output computing means computes the first gas turbine output, the second gas turbine output, and the fourth gas turbine output according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, and an atmospheric pressure ratio equivalent to a ratio between the intake pressure of the compressor and a standard atmospheric pressure or according to the intake-air temperature of the compressor, the aperture of the inlet guide vane, the turbine bypass ratio, and the atmospheric pressure ratio.
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