Method of selective combustor control for reduced emissions

Patent metadata

Field	Value
Publication number	US-11067279-B2
Application number	US-201616300637-A
Country	US
Kind code	B2
Filing date	May 12, 2016
Priority date	May 12, 2016
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

A method, including: operating an industrial gas turbine engine having a plurality of combustor cans arranged in an annular array, each can having burner stages and a pilot burner arrangement having a premix pilot burner and a diffusion pilot burner; operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.

First claim

The invention claimed is:

1. A method of operating an industrial gas turbine during a transition from a uniform combustion mode to a hot/warm combustion mode, the industrial gas turbine comprising:
combustor cans arranged in an annular array, each combustor can comprising:
a burner stage; and
a pilot burner arrangement, each pilot burner arrangement comprising:
a premix pilot burner; and
a diffusion pilot burner;

the method comprising:
operating the industrial gas turbine in the uniform combustion mode, wherein in the uniform combustion mode each combustor can operates under the same operating conditions, wherein combustion gases exiting the combustor cans exhibit a uniform temperature;
operating the industrial gas turbine in a transfer combustion mode during the transition from the uniform combustion mode to the hot/warm combustion mode; and
operating the industrial gas turbine in the hot/warm combustion mode, wherein the hot/warm combustion mode is an asymmetric combustion mode, wherein at least one combustor can is a warm combustor can that produces warm combustion and the remaining combustor cans are hot combustor cans that produce hot combustion, wherein combustion gases exiting the hot combustor cans exhibit a higher temperature than the uniform temperature and combustion gases exiting the at least one warm combustor can exhibit a lower temperature than the uniform temperature;
the transfer combustion mode comprising:
initially increasing a rate of fuel flow to the diffusion pilot burner in the at least one warm combustor can;
stopping fuel flow to the burner stage in the at least one warm combustor can; and
subsequently decreasing the rate of fuel flow to the diffusion pilot burner in the at least one warm combustor can while maintaining a same total fuel flow to the pilot burner arrangement in the at least one warm combustor can by increasing a rate of fuel flow to the premix pilot burner in the at least one warm combustor can.

2. The method of claim 1 , the transfer combustion mode further comprising:
maintaining a total fuel flow to the combustor cans equal to a total fuel flow to the combustor cans during the uniform combustion mode.

3. The method of claim 1 , the transfer combustion mode further comprising:
decreasing a rate of fuel flow to each diffusion pilot burner in the hot combustor cans from a rate of fuel flow that occurs during the uniform combustion mode to a reduced rate of fuel flow that occurs during the hot/warm combustion mode.

4. The method of claim 1 , wherein:
a rate of fuel flow to the pilot burner arrangement of the at least one warm combustor can is higher in the hot/warm combustion mode than in the uniform combustion mode.

5. The method of claim 1 , the transfer combustion mode further comprising:
decreasing a rate of fuel flow to each pilot burner arrangement of the hot combustor cans from a rate of fuel flow that occurs during the uniform combustion mode to a decreased rate of fuel flow that occurs during the hot/warm combustion mode.

6. A method of operating an industrial gas turbine during a transition from a hot/warm combustion mode to a uniform combustion mode, the industrial gas turbine comprising:
combustor cans arranged in an annular array, each combustor can comprising:
a burner stage; and
a pilot burner arrangement, each pilot burner arrangement comprising:
a premix pilot burner; and
a diffusion pilot burner;

the method comprising:
operating the industrial gas turbine in the hot/warm combustion mode, wherein the hot/warm combustion mode is an asymmetric combustion mode, wherein at least one combustor can is a warm combustor can that produces warm combustion and the remaining combustor cans are hot combustor cans that produce hot combustion, wherein combustion gases exiting the hot combustor cans exhibit a higher temperature than a uniform temperature and combustion gases exiting the at least one warm combustor can exhibit a lower temperature than the uniform temperature;
operating the industrial gas turbine in a transfer combustion mode during the transition from the hot/warm combustion mode to the uniform combustion mode; and
operating the industrial gas turbine in the uniform combustion mode, wherein in the uniform combustion mode each combustor can operates under the same operating conditions, wherein combustion gases exiting the combustor cans exhibit the uniform temperature;
the transfer combustion mode comprising:
initially increasing a rate of fuel flow to the diffusion pilot burner in the at least one warm combustor can while maintaining a same total fuel flow to the pilot burner arrangement in the at least one warm combustor can by decreasing a rate of fuel flow to the premix pilot burner in the at least one warm combustor can;
starting fuel flow to the burner stage in the at least one warm combustor can; and
subsequently decreasing the rate of fuel flow to the diffusion pilot burner in the at least one warm combustor can.

7. The method of claim 6 , the transfer combustion mode further comprising:
increasing a rate of fuel flow to each diffusion pilot burner in the hot combustor cans from a rate of fuel flow that occurs during hot combustion to an increased rate of fuel flow that occurs during the uniform combustion mode.

8. The method of claim 6 , wherein:
a rate of fuel flow to the pilot burner arrangement of the at least one warm combustor can is higher in the hot/warm combustion mode than in the uniform combustion mode.

9. The method of claim 6 , the transfer combustion mode further comprising:
increasing a rate of fuel flow to each pilot burner arrangement of the hot combustor cans from a rate of fuel flow that occurs during hot combustion to an increased rate of fuel flow that occurs during the uniform combustion mode.

Assignees

• Siemens Ag
• Siemens Energy Global Gmbh & Co Kg

Inventors

• Johnson Clifford E
• Cai Weidong
• Miduturi Krishna C
• Karanja Ben
• Huth Michael
• Krebs Werner
• Seifarth Mark
• Primke Thomas
• Ghermay Yohannes

Classifications

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F02C9/34

  Joint control of separate flows to main and auxiliary burners · CPC title

• F02C7/228

  Dividing fuel between various burners · CPC title

• F23R3/286 Primary

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

• F05D2270/31

  Fuel schedule for stage combustors · CPC title