초록 ▼

A system 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 system 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 controller in a gas turbine having a compressor, combustor and turbine, said controller comprising: a sensor input receiving data regarding an actual turbine exhaust temperature, a compressor pressure ratio level, a compressor pressure inlet loss, a turbine back press

The invention claimed is: 1. A controller in a gas turbine having a compressor, combustor and turbine, said controller comprising: a sensor input receiving data regarding an actual turbine exhaust temperature, a compressor pressure ratio level, a compressor pressure inlet loss, a turbine back pressure level and ambient humidity; a processor executing a program, wherein said program further comprises: a compressor schedule for generating a first target exhaust temperature based on the compressor pressure ratio level, and at least one additional schedule for generating a temperature change to be applied to the first target turbine exhaust temperature wherein the temperature change is derived from at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and the turbine back pressure level, and wherein said processor outputs a modified target exhaust temperature based on the first target exhaust temperature and the temperature change, and said controller outputs a combustor control signal based on the modified target exhaust temperature. 2. A controller as in claim 1 wherein the at least one additional schedule includes a humidity verses delta target exhaust temperate schedule having an input indicative of the ambient humidity. 3. A controller as in claim 1 wherein the at least one additional schedule includes a compressor inlet pressure loss verses delta target exhaust temperate schedule having inputs indicative of the compressor pressure ratio level and the compressor pressure inlet loss. 4. A controller as in claim 1 wherein the at least one additional schedule includes a turbine back pressure verses delta target exhaust temperate schedule having inputs indicative of the compressor pressure ratio level and the back pressure level. 5. A controller as in claim 1 further comprising a combustion controller outputting the combustor control signal. 6. A system for determining a target exhaust temperature for a gas turbine comprising: means for determining a target exhaust temperature based on a compressor pressure condition; means for 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 means for adjusting the target exhaust temperature by applying the temperature adjustment. 7. A system as in claim 6 wherein the means for determining the temperature adjustment applies a schedule having a delta specific humidity input and a delta exhaust temperature output, wherein the delta specific humidity input is a difference between an actual specific humidity at an inlet to the gas turbine and a predefined specific humidity level, and the delta exhaust temperature output is a temperature difference to be summed with the target exhaust temperature. 8. A system as in claim 6 wherein the means for determining the temperature adjustment applies a schedule having inputs of delta inlet pressure loss and the current compressor condition, and an output of a delta exhaust temperature output, wherein the delta inlet pressure loss input is a difference between an actual inlet pressure loss to the gas turbine and a predefined inlet pressure loss level, and the delta exhaust temperature output is a temperature difference to be summed with the target exhaust temperature. 9. A system as in claim 6 wherein the means for determining the temperature adjustment applies a schedule having inputs of delta back pressure and the current compressor condition, and an output of a delta exhaust temperature output, wherein the delta back pressure input is a difference between an actual back pressure to the gas turbine and a predefined back pressure level, and the delta exhaust temperature output is a temperature difference to be summed with the target exhaust temperature. 10. A system as in claim 6 wherein the target exhaust temperature is applied by a gas turbine controller to determine a turbine firing temperature. 11. A system as in claim 6 wherein the target exhaust temperature is applied by a gas turbine controller to determine a fuel flow to a combustor of the gas turbine. 12. A system in claim 6 wherein the compressor pressure condition is compressor pressure ratio. 13. A controller in a gas turbine having a compressor, combustor and turbine, said controller comprising: a input receiving data regarding a sensed turbine exhaust temperature, a compressor pressure ratio level, a compressor pressure inlet loss, a turbine back pressure level and ambient humidity; a processor executing a program, wherein said program further comprises: a compressor schedule for generating a first target exhaust temperature based on the compressor pressure ratio level and at least one additional schedule for generating a temperature change to be applied to the first target turbine exhaust temperature wherein the temperature change is derived from at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine back pressure level, and wherein said processor outputs a modified target exhaust temperature based on the first target exhaust temperature and the temperature change, and said controller outputs a combustor control signal based on the modified target exhaust temperature. 14. A controller as in claim 13 wherein said controller further comprises a combustion controller outputting the combustor control signal based on the modified target exhaust temperature. 15. A controller as in claim 13 wherein the at lease one additional schedule further comprises a delta specific humidity input and a delta exhaust temperature output, wherein the delta specific humidity input is a difference between an actual specific humidity at an inlet to the gas turbine and a predefined specific humidity level, and the delta exhaust temperature output is a temperature difference summed with the adjusted target turbine exhaust temperature. 16. A controller as in claim 13 wherein the at lease one additional schedule further comprises inputs of delta inlet pressure loss and the current compressor pressure ratio and an output of a delta exhaust temperature output, wherein the delta inlet pressure loss input is a difference between an actual inlet pressure loss to the gas turbine and a predefined inlet pressure loss level, and the delta exhaust temperature output is summed with target turbine exhaust. 17. A controller as in claim 13 wherein the at least one additional schedule further comprises inputs of delta back pressure and the current compressor condition, and an output of a delta exhaust temperature output, wherein the delta back pressure input is a difference between an actual back pressure to the gas turbine and a predefined back pressure level, and the delta exhaust temperature output is summed with target turbine exhaust. 18. A controller as in claim 13 wherein the target turbine exhaust temperature is applied by the controller to determine a turbine firing temperature. 19. A controller as in claim 13 wherein the target turbine exhaust temperature is applied by the controller to determine a fuel flow to a combustor of the gas turbine. 20. A controller as in claim 13 wherein said gas turbine is an industrial gas turbine.