초록 ▼

A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consis

A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.

대표청구항 ▼

The invention claimed is: 1. A method for adjusting a base fuel split schedule for a gas turbine combustor comprising: a. determining a corrected target turbine exhaust temperature based on a compressor pressure condition; b. determining a first corrected temperature adjustment to the corrected tar

The invention claimed is: 1. A method for adjusting a base fuel split schedule for a gas turbine combustor comprising: a. determining a corrected target turbine exhaust temperature based on a compressor pressure condition; b. determining a first corrected temperature adjustment to the corrected target exhaust temperature based on at least one parameter of a group of parameters consisting of compressor inlet pressure loss and turbine exhaust back pressure; c. determining a second corrected temperature adjustment to the corrected target exhaust temperature based on a nitrogen oxide (NOx) limiting requirement and the base fuel split command; d. determining an adjusted corrected target exhaust temperature based on the first corrected temperature adjustment and the second corrected temperature adjustment; e. determining an uncorrected adjusted target exhaust temperature based on a temperature of a discharge of a compressor of the gas turbine and the adjusted corrected target exhaust temperature; f. determining a temperature difference between the uncorrected adjusted target exhaust temperature and an uncorrected target exhaust temperature selected from a combustor temperature leveling algorithm, and g. applying the temperature difference to generate an adjusted fuel split schedule. 2. A method as in claim 1 wherein the uncorrected adjusted target exhaust temperature is further based on an uncorrected temperature adjustment determined from ambient specific humidity. 3. A method as in claim 1 wherein the difference between the uncorrected adjusted corrected target exhaust temperature and an uncorrected target exhaust temperature is limited to a positive value. 4. A method as in claim 1 wherein the adjusted fuel split schedule further comprises an adjusted first fuel split indicating a portion of fuel flow to a primary fuel nozzle in the combustor and an adjusted second fuel split indicating a portion of the fuel flow to be mixed with secondary air entering the combustor. 5. A method as in claim 1 wherein the base fuel split schedule is determined for a base load condition at which the gas turbine is operating at full rated power. 6. A method as in claim 1 wherein steps (b) through (g) are performed in connection with a nitrogen oxide (NOx) leveling algorithm. 7. A method as in claim 1 wherein the application of the difference further comprises: deriving an adjusted projected NOx level from the temperature difference; generating a Q factor as a ratio of a NOx emission baseline and the adjusted projected NOx level; applying the Q factor to the base fuel split schedule to generate the adjusted fuel split schedule. 8. A method as in claim 7 further comprising determining the adjusted NOx level from a corrected value of the temperature difference. 9. A method as in claim 1 wherein each step of the method is performed automatically. 10. A method as in claim 1 wherein the fuel split level is a plurality of fuel split levels each indicating a portion of fuel flow to one of a plurality of zones of fuel nozzles in the combustor. 11. A method as in claim 1 wherein the fuel split schedule is a schedule for fuel splits to all combustors in the gas turbine. 12. A method for adjusting a base fuel split schedule for a gas turbine combustor comprising: a. automatically determining a corrected target turbine exhaust temperature based on a compressor pressure condition; b. automatically determining a first corrected temperature adjustment to the corrected target exhaust temperature based on at least one parameter of a group of parameters consisting of compressor inlet pressure loss and turbine exhaust back pressure; c. automatically determining a second corrected temperature adjustment to the corrected target exhaust temperature based on a nitrogen oxide (NOx) limiting requirement and the base fuel split command; d. automatically determining an adjusted corrected target exhaust temperature based on the first corrected temperature adjustment and the second corrected temperature adjustment; e. automatically determining an uncorrected adjusted target exhaust temperature based on a temperature of a discharge of a compressor of the gas turbine and the adjusted corrected target exhaust temperature; f. automatically determining a temperature difference between the uncorrected adjusted target exhaust temperature and an uncorrected target exhaust temperature selected from a combustor temperature leveling algorithm, and g. automatically applying the temperature difference to generate an adjusted fuel split schedule. 13. A method as in claim 12 wherein the uncorrected adjusted target exhaust temperature is further based on an uncorrected temperature adjustment determined from ambient specific humidity. 14. A method as in claim 12 wherein the temperature difference between the uncorrected adjusted corrected target exhaust temperature and an uncorrected target exhaust temperature is limited to a positive value. 15. A method as in claim 12 wherein the adjusted fuel split schedule further comprises an adjusted first fuel split indicating a portion of fuel flow to a primary fuel nozzle in the combustor and an adjusted second fuel spit indicating a portion of the fuel flow to be mixed with secondary air entering the combustor. 16. A method as in claim 12 wherein the base fuel split schedule is determined for a base load condition at which the gas turbine is operating at full rated power. 17. A method as in claim 12 wherein steps (b) through (g) are performed in connection with a nitrogen oxide (NOx) leveling algorithm. 18. A method as in claim 12 wherein the application of the difference further comprises: deriving an adjusted projected NOx level from the temperature difference; generating a Q factor as a ratio of a NOx emission baseline and the adjusted projected NOx level; applying the Q factor to the base fuel split schedule to generate the adjusted fuel split schedule. 19. A method as in claim 18 further comprising determining the adjusted NOx level from a corrected value of the temperature difference. 20. A method as in claim 1 wherein the fuel split level is a plurality of fuel split levels each indicating a portion of fuel flow to one of a plurality of zones of fuel nozzles in the combustor.