대표
청구항
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What is claimed is: 1. A gas turbine system comprising: a gas turbine engine including: an annular combustor, and a turbine driven by combustion gas from said annular combustor to rotate on a longitudinal centerline axis of said gas turbine engine; and a controller, wherein said annular combustor comprises: an outer casing; a liner disposed in said outer casing; and a plurality of dilution air regulators introducing dilution air into said liner, said plurality of dilution air regulators being circumscribed about said longitudinal centerline axis and sp...
What is claimed is: 1. A gas turbine system comprising: a gas turbine engine including: an annular combustor, and a turbine driven by combustion gas from said annular combustor to rotate on a longitudinal centerline axis of said gas turbine engine; and a controller, wherein said annular combustor comprises: an outer casing; a liner disposed in said outer casing; and a plurality of dilution air regulators introducing dilution air into said liner, said plurality of dilution air regulators being circumscribed about said longitudinal centerline axis and spaced apart at substantially equal intervals, and wherein said controller individually controls said plurality of dilution air regulators to individually adjust dilution air flows through each of said plurality of dilution air regulators into said liner. 2. The gas turbine system according to claim 1, further comprising: a plurality of turbine outlet temperature sensors disposed at a turbine outlet of said turbine to measure turbine outlet temperatures at positions thereof, said plurality of turbine outlet temperature sensors being circumscribed about said longitudinal centerline axis, and spaced apart at equal intervals, wherein said controller adjusts said dilution air flows in response to said turbine outlet temperatures. 3. The gas turbine system according to claim 2, further comprising: a combustor inlet state sensor disposed at an inlet of said annular combustor to obtain a state of said combustor inlet, wherein said controller includes a dilution air flow instruction producing unit producing a plurality of eventual dilution air flow instructions respectively associated with said plurality of dilution air regulators, wherein said dilution air flow instruction producing unit comprises: a first module producing a plurality of feedback-based dilution flow instructions through an isochronous feedback control in response to said turbine outlet temperatures, a second module which establishes a self-organized map in response to said eventual dilution air flow instructions and said state of said combustor inlet, and produces a plurality of SOM-based dilution air flow instructions using an SOM algorithm based on said self-organized map, and a third module producing said plurality of eventual dilution air flow instructions from said plurality of feedback-based and SOM-based dilution air flow instructions, and wherein said plurality of dilution air regulators respectively introduce said dilution air into said liner in response to said plurality of eventual dilution air flow instructions associated therewith. 4. The gas turbine engine system according to claim 2, further comprising: a rotation speed sensor measuring a rotation speed of said turbine, an temperature sensor measuring a combustor inlet temperature, and a pressure sensor measuring a combustor inlet pressure, wherein said controller includes a dilution air flow instruction producing unit producing a plurality of eventual dilution air flow instructions respectively associated with said plurality of dilution air regulators, wherein said dilution air flow instruction producing unit comprises: a first module producing a plurality of feedback-based dilution air flow instructions through an isochronous feedback control in response to said turbine outlet temperatures, a second module which establishes a self-organized map in response to said eventual dilution air flow instructions, said rotation speed of said turbine, said combustor inlet temperature, and said combustor inlet pressure, and produces a plurality of SOM-based dilution air flow instructions using an SOM algorithm based on said self-organized map, and a third module producing said plurality of eventual dilution air flow instructions from said plurality of feedback-based and SOM-based dilution air flow instructions, and wherein said plurality of dilution air regulators respectively introduce said dilution air into said liner in response to said plurality of eventual dilution air flow instructions associated therewith. 5. A gas turbine system comprising: a gas turbine engine including an annular combustor, and a turbine driven by combustion gas from said annular combustor to rotate on a longitudinal centerline axis of said gas turbine engine; a plurality of fuel flow regulators; and a controller, wherein said annular combustor comprises: an outer casing, a liner disposed in said outer casing, a plurality of fuel nozzles circumscribed about said longitudinal centerline axis, and spaced apart at substantially equal intervals, and a plurality of dilution air regulators introducing dilution air into said liner, said plurality of dilution air regulators being circumscribed about said longitudinal centerline axis and spaced apart at substantially equal intervals, wherein said plurality of fuel flow regulators respectively feed fuel to said plurality of fuel nozzles, and wherein said controller individually controls said plurality of dilution air regulators to individually adjust dilution air flows through each of said plurality of dilution air regulators into said liner, and individually controls said plurality of fuel flow regulators to individually adjust fuel flows into each of said plurality of fuel nozzles. 6. The gas turbine system according to claim 5, further comprising: a plurality of environmental pollutant sensor units disposed at a turbine outlet of said turbine to measure respective emission levels of environmental pollutant at positions thereof, said environmental pollutant sensor units being circumscribed about said longitudinal centerline axis and spaced apart at substantially equal intervals, a plurality of turbine outlet temperature sensors disposed at a turbine outlet of said turbine to measure turbine outlet temperatures at positions thereof, said plurality of turbine outlet temperature sensors being circumscribed about said longitudinal centerline axis, and spaced apart at equal intervals, wherein said controller adjusts said dilution air flows in response to said turbine outlet temperatures, and adjusts said fuel flows in response to said emission levels of said environmental pollutant. 7. The gas turbine system according to claim 6, wherein each of said plurality of environmental pollutant sensor units includes: a NOx sensor measuring a NOx emission level, and a CO sensor measuring a CO emission level, and wherein said controller adjusts said fuel flows in response to said NOx emission levels and said CO emission levels. 8. The gas turbine system according to claim 7, wherein said controller calculates a set of emission indices through an emission evaluation function which includes a first term dependent on a logarithm of said NOx emission levels, and a second term dependent on a logarithm of said CO emission levels, and wherein said controller adjusts said fuel flows in response to said set of emission indices. 9. The gas turbine system according to claim 6, wherein each of said plurality of environmental pollutant sensor units includes: a NOx sensor measuring a NOx emission level, and an UHC (unburned hydrocarbon) sensor measuring an UHC emission level, and wherein said controller adjusts said fuel flows in response to said NOx emission levels and said UHC emission levels. 10. The gas turbine system according to claim 9, wherein said controller calculates a set of emission indices through an emission evaluation function which includes a first term dependent on a logarithm of said NOx emission levels, and a second term dependent on a logarithm of said UHC emission levels, and wherein said controller adjusts said fuel flows in response to said set of emission indices. 11. The gas turbine engine system according to claim 6, further comprising: a rotation speed sensor measuring a rotation speed of said turbine, an temperature sensor measuring a combustor inlet temperature, and a pressure sensor measuring a combustor inlet pressure, wherein said controller includes an instruction producing unit producing a plurality of eventual fuel flow instructions respectively associated with said plurality of fuel nozzles, and a plurality of eventual dilution air flow instructions respectively associated with said plurality of dilution air regulators, and, wherein said instruction producing unit comprises: a first module producing a plurality of feedback-based fuel flow instructions through an isochronous feedback control in response to said emission levels of said environmental pollutant, a second module producing a plurality of feedback-based dilution air flow instructions through another isochronous feedback control in response to said turbine outlet temperatures, a third module which establishes a self-organized map in response to said eventual fuel flow instructions, said eventual dilution air flow instructions, said rotation speed of said turbine, said combustor inlet temperature, and said combustor inlet pressure, and produces a plurality of SOM based fuel flow instructions, and a plurality of SOM-based dilution air flow instructions using an SGM algorithm based on said self-organized map, and a fourth module producing said plurality of eventual fuel flow instructions from said plurality of feedback-based and SOM-based fuel flow instructions, while producing said plurality of eventual dilution air flow instructions from said plurality of feedback-based and SOM-based dilution air flow instructions, wherein said plurality of fuel flow regulators respectively feed said fuel to said plurality of fuel nozzles in response to said plurality of eventual fuel flow instructions associated therewith, and wherein said plurality of dilution air regulators respectively introduce said dilution air into said liner in response to said plurality of eventual dilution air flow instructions associated therewith. 12. A gas turbine system comprising: a gas turbine engine including: an annular combustor comprising a plurality of fuel nozzles circumscribed about an longitudinal centerline axis of said gas turbine engine, and spaced apart at substantially equal intervals, and a turbine driven by combustion gas from said annular combustor to rotate on said longitudinal centerline axis; a plurality of fuel flow regulators respectively feeding fuel to said plurality of fuel nozzles; a controller individually controlling said plurality of fuel flow regulators to individually adjust fuel flows into each of said fuel nozzles; and a plurality of environmental pollutant sensor units disposed at a turbine outlet of said turbine to measure respective emission levels of environmental pollutant at positions thereof, said environmental pollutant sensor units being circumscribed about said longitudinal centerline axis and spaced apart at substantially equal intervals, wherein said controller adjusts said fuel flows in response to said emission levels of said environmental pollutant, and wherein each of said plurality of environmental pollutant sensor units includes: a NOx sensor measuring a NOx emission level, and a CO sensor measuring a CO emission level, and wherein said controller adjusts said fuel flows in response to said NOx emission levels and said CO emission levels. 13. A gas turbine system comprising: a gas turbine engine including: an annular combustor comprising a plurality of fuel nozzles circumscribed about an longitudinal centerline axis of said gas turbine engine, and spaced apart at substantially equal intervals, and a turbine driven by combustion gas from said annular combustor to rotate on said longitudinal centerline axis; a plurality of fuel flow regulators respectively feeding fuel to said plurality of fuel nozzles; a controller individually controlling said plurality of fuel flow regulators to individually adjust fuel flows into each of said fuel nozzles; and a plurality of environmental pollutant sensor units disposed at a turbine outlet of said turbine to measure respective emission levels of environmental pollutant at positions thereof, said environmental pollutant sensor units being circumscribed about said longitudinal centerline axis and spaced apart at substantially equal intervals, wherein said controller adjusts said fuel flows in response to said emission levels of said environmental pollutant, wherein each of said plurality of environmental pollutant sensor units includes: a NOx sensor measuring a NOx emission level, and an UHC (unburned hydrocarbon) sensor measuring an UHC emission level, and wherein said controller adjusts said fuel flows in response to said NOx emission levels and said UHC emission levels. 14. A gas turbine system comprising: a gas turbine engine including: an annular combustor comprising a plurality of fuel nozzles circumscribed about an longitudinal centerline axis of said gas turbine engine, and spaced apart at substantially equal intervals, and a turbine driven by combustion gas from said annular combustor to rotate on said longitudinal centerline axis; a plurality of fuel flow regulators respectively feeding fuel to said plurality of fuel nozzles; a controller individually controlling said plurality of fuel flow regulators to individually adjust fuel flows into each of said fuel nozzles; a plurality of environmental pollutant sensor units disposed at a turbine outlet of said turbine to measure respective emission levels of environmental pollutant at positions thereof, said environmental pollutant sensor units being circumscribed about said longitudinal centerline axis and spaced apart at substantially equal intervals, wherein said controller adjusts said fuel flows in response to said emission levels of said environmental pollutant; and a combustor inlet state sensor disposed at an inlet of said combustor to obtain a state of said combustor inlet, wherein said controller includes a fuel flow instruction producing unit producing a plurality of eventual fuel flow instructions respectively associated with said plurality of fuel nozzles, wherein said fuel flow instruction producing unit comprises: a first module producing a plurality of feedback-based fuel flow instructions through an isochronous feedback control in response to said emission levels of said environmental pollutant, a second module which establishes a self-organized map in response to said eventual fuel flow instructions and said state of said combustor inlet, and produces a plurality of SOM-based fuel flow instructions using an SOM algorithm based on said self-organized map, and a third module producing said plurality of eventual fuel flow instructions from said plurality of feedback-based and SOM-based fuel flow instructions, and wherein said plurality of fuel flow regulators respectively feed said fuel to said plurality of fuel nozzles in response to said plurality of eventual fuel flow instructions associated therewith. 15. A gas turbine engine system comprising: a gas turbine engine including: an annular combustor comprising a plurality of fuel nozzles circumscribed about an longitudinal centerline axis of said gas turbine engine, and spaced apart at substantially equal intervals, and a turbine driven by combustion gas from said annular combustor to rotate on said longitudinal centerline axis; a plurality of fuel flow regulators respectively feeding fuel to said plurality of fuel nozzles; a controller individually controlling said plurality of fuel flow regulators to individually adjust fuel flows into each of said fuel nozzles; and a plurality of environmental pollutant sensor units disposed at a turbine outlet of said turbine to measure respective emission levels of environmental pollutant at positions thereof, said environmental pollutant sensor units being circumscribed about said longitudinal centerline axis and spaced apart at substantially equal intervals, wherein said controller adjusts said fuel flows in response to said emission levels of said environmental pollutant; a rotation speed sensor measuring a rotation speed of said turbine; an temperature sensor measuring a combustor inlet temperature; and a pressure sensor measuring a combustor inlet pressure, wherein said controller includes a fuel flow instruction producing unit producing a plurality of eventual fuel flow instructions respectively associated with said plurality of fuel nozzles, wherein said fuel flow instruction producing unit comprises: a first module producing a plurality of feedback-based fuel flow instructions through an isochronous feedback control in response to said emission levels of said environmental pollutant; a second module which establishes a self-organized map in response to said eventual fuel flow instructions, said rotation speed of said turbine, said combustor inlet temperature, and said combustor inlet pressure, and produces a plurality of SOM-based fuel flow instructions using an SOM algorithm based on said self-organized map; and a third module producing said plurality of eventual fuel flow instructions from said plurality of feedback-based and SOM-based fuel flow instructions, and wherein said plurality of fuel flow regulators respectively feed said fuel to said plurality of fuel nozzles in response to said plurality of eventual fuel flow instructions associated therewith. 16. A method for operating a gas turbine engine comprising: providing a gas turbine engine including: an annular combustor comprising: an outer casing; a liner disposed in said outer casing; a plurality of dilution air regulators introducing dilution air into said liner, said plurality of dilution air regulators being circumscribed about a longitudinal centerline axis of said gas turbine engine and spaced apart at equal intervals, and a turbine driven by combustion gas from said annular combustor to rotate on said longitudinal centerline axis, individually adjusting dilution air flows through each of said plurality of dilution air regulators.
