US 7,024,862 B2 · System and method for controlling combustion in gas turbine with annular combustor

Abstract

A gas turbine system composed of a gas turbine engine and a controller. The gas turbine engine includes an annular combustor, and a turbine driven by combustion gas from the annular combustor to rotate on a longitudinal centerline axis of the gas turbine engine. The annular combustor is comprised of an outer casing, a liner disposed in the outer casing, and a plurality of dilution air regulators introducing dilution air into the liner. The plurality of dilution air regulators are circumscribed about the longitudinal centerline axis and spaced apart at substantially equal intervals. The controller controls the plurality of dilution air regulators to individually adjust dilution air flows through the plurality of dilution air regulators into the liner.

Claims16

Dependent claims

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.

8 more elements

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.

8 more elements

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.

11 more elements

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.

15 more elements

Dependencies are inferred from the claim text.

System and method for controlling combustion in gas turbine with annular combustor

Life of this patent

System and method for controlling combustion in gas turbine with annular combustor

Life of this patent

Abstract

Claims16