Low partial load emission control for gas turbine system

Patent metadata

Field	Value
Publication number	US-10920676-B2
Application number	US-201615353836-A
Country	US
Kind code	B2
Filing date	Nov 17, 2016
Priority date	Nov 17, 2016
Publication date	Feb 16, 2021
Grant date	Feb 16, 2021

Abstract

A combustor system for a GT system may include: a plurality of burners, each burner including an inflow region for receiving a combustion air flow and a mixing zone disposed downstream of the inflow region for receiving the air flow and a fuel flow; a combustion chamber disposed downstream of the mixing zone; a fuel flow valve system disposed to control the fuel flow to each of the plurality of burners; a combustion sensor configured to determine a combustion parameter; and an exhaust sensor configured to determine an exhaust parameter. A control system may be connected to the combustion sensor, the exhaust sensor and fuel flow valve system. The control system, in response to the gas turbine system operating at a low partial load, redistributes the fuel flow to at least one burner of the plurality of burners as a function of a predetermined emission limit.

First claim

What is claimed is:

1. A combustor system for a gas turbine system, comprising:
a plurality of burners, each burner of the plurality of burners including an inflow region for receiving a combustion air flow and a corresponding mixing zone disposed downstream of the inflow region for receiving the air flow and a fuel flow;
a combustion chamber disposed downstream of the corresponding mixing zone of each burner of the plurality of burners;
a fuel flow vale system disposed to control the fuel flow received in the corresponding mixing zone of each burner of the plurality of burners;
a combustion sensor configured to determine a combustion parameter;
an exhaust sensor configured to determine an exhaust parameter; and
a control system operatively coupled to the combustion sensor, the exhaust sensor and the fuel flow valve system, the control system configured to, in response to a load of the gas turbine system decreasing, perform a redistribution of the fuel flow received in the corresponding mixing zone of at least one burner of the plurality of burners as a function of a predetermined emission limit,
wherein the fuel flow vale system includes:
a first flow control structure that includes at least one burner group control valve, the at least one burner group control vale disposed to turn off the fuel flow received in the corresponding mixing zones of a selected group of the plurality of burners in order to perform the redistribution:
a second flow control structure that includes a first single burner control valve, the first single burner control valve disposed to turn off the fuel flow received in the corresponding mixing zone of a first selected single burner of the plurality of burners in order to perform the redistribution; and
a third flow control structure that includes a second single burner control valve operatively coupled to a flow limiter, the flow limiter disposed to selectively limit the fuel flow received in the corresponding mixing zone of a second selected single burner of the plurality of burners to a predetermined value in order to perform the redistribution, and
wherein the first single burner control valve is not operatively coupled to the flow limiter.

2. The combustor system of claim 1 , wherein the combustion parameter includes a combustor pulsation value, and the exhaust parameter includes at least one of: a temperature after turbine (TAT) and an emission value of the gas turbine system.

3. The combustor system of claim 1 , wherein the control system controls the fuel flow received in the corresponding mixing zone of the at least one burner as a function of a temperature after turbine control function that controls a temperature after turbine (TAT),
wherein the temperature after turbine control function is responsive to at least one of: a turbine inlet temperature (TIT), a compressor inlet temperature of a compressor of the gas turbine system (TK 1 ), and a variable inlet guide vane (VIGV) position that controls an air flow from the compressor.

4. The combustor system of claim 1 , wherein the predetermined emission limit includes a first emission limit and a second emission limit, and
wherein the control system is configured to, in response to the load of the gas turbine system decreasing to a first partial load, activate the at least one burner group control valve, wherein the load decreasing to the first partial load causes at least one of the following:
a turbine inlet temperature (TIT) decreasing to a first TIT set point,
a combustor pulsation value increasing to a first pulsation set point, or
an emission value of the gas turbine system exceeding the first emission limit.

5. The combustor system of claim 4 , wherein the control system is configured to adjust a target temperature after turbine of a temperature after turbine control function to lower the target temperature after turbine, in further response to the load of the gas turbine system decreasing to the first partial load.

6. The combustor system of claim 4 , wherein the control system is further configured to, in response to a variable inlet guide vane (VIGV) position reaching an adjustment limit and the load of the gas turbine system further decreasing to a second partial load lower than the first partial load, activate one or both of: the first single burner control valve and the flow limiter, wherein the load decreasing to the second partial load causes at least one of the following:
the turbine inlet temperature (TIT) decreasing to a second TIT set point,
the combustor pulsation value increasing to a second pulsation set point, or
the emission value exceeding the second emission limit.

7. The combustor system of claim 1 , wherein the predetermined emission limit includes a first emission limit and a second emission limit, and the control system is further configured to, in response to a variable inlet guide vane (VIGV) position not reaching an adjustment limit and the load of the gas turbine system decreasing to a second partial load lower than a first partial load, activate one or both of: the first single burner control valve and the flow limiter, wherein the load decreasing to the second partial load causes an emission value of the gas turbine system to exceed one or both of the first and the second emission limits.

8. The combustor system of claim 4 , wherein the control system is configured to, in response to the load of the gas turbine system increasing, deactivate at least one of: the at least one burner group control valve, the first single burner control valve, or the flow limiter, wherein the load increasing causes at least one of the following: the turbine inlet temperature (TIT) increasing to exceed the first TIT set point, the turbine inlet temperature (TIT) increasing to exceed a second TIT set point, the combustor pulsation value decreasing to below the first pulsation set point, the combustor pulsation value decreasing to below a second pulsation set point, the emission value decreasing to below the first emission limit, or the emission value decreasing to below the second emission limit.

9. The combustor system of claim 1 , wherein the load decreasing includes the load decreasing to a load of less than 50%.

10. A control system, the control system configured for a combustor system of a gas turbine system comprising plurality of burners, each burner of the plurality of burners including an inflow region for receiving a combustion air flow and a corresponding mixing zone disposed downstream of the inflow region for receiving the air flow and a fuel flow, the control system comprising:
a computerized controller operatively coupled to:
a combustion sensor configured to determine a combustion parameter within a combustion chamber of the combustor system,
an exhaust sensor configured to determine an exhaust parameter of exhaust exiting the gas turbine system, and
a fuel flow vale system disposed to control the fuel flow received in the corresponding mixing zone of each burner of the plurality of burners of the combustor system,

wherein the computerized controller is configured to, in response to a load of the gas turbine system decreasing, perform a redistribution of the fuel flow received in the corresponding mixing zone of at least one burner of the plurality of burners as a function of a predetermined emission limit, and
wherein the fuel flow vale system includes:
a first flow control structure that includes at least one burner group control valve, the at least one burner group control vale disposed to turn off the fuel flow received in the corresponding mixing zones of a selected group of the plurality of burners in order to perform the redistribution;
a second flow control structure that inc

Assignees

• Gen Electric

Inventors

• Sorato Sebastiano
• Axford Lindsay Dawn
• Grimm Frank
• Lechner Andreas
• Mettler Adrian

Classifications

• F02C9/48 Primary

  Control of fuel supply conjointly with another control of the plant (with nozzle section control F02K1/17) · CPC title

• Y02E20/16

  Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT] · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23N5/02

  using devices responsive to thermal changes or to thermal expansion of a medium · CPC title

• F23N5/003

  using detectors sensitive to combustion gas properties (F23N5/02, F23N5/18 - F23N5/26 take precedence) · CPC title