Method to operate a combustor of a gas turbine
View Patent ↗A method to operate a combustor of a gas turbine is provided. The method includes monitoring the combustion gas temperature by temperature measurements downstream said combustor to measure a respective combustion gas temperature at different locations at respectively equal flow-distances to the burner of the combustion gas, comparing the temperature measurements, opening a valve or increasing the opening position of the valve to control the portion of oxygen containing gas to be tapped off when the comparison reveals that a difference between the temperature measurements exceeds a temperature difference threshold ΔT 1.
1. A method of operating a combustor of a gas turbine engine, wherein the gas turbine engine comprises a compressor, said combustor, and a turbine,
wherein said compressor delivers an oxygen containing gas to said combustor, wherein said combustor comprises at least two burners and at least one main combustion chamber downstream of said at least two burners,
wherein at least two of said at least two burners join commonly into said at least one main combustion chamber to generate combustion gas from burning fuel and said oxygen containing gas,
wherein one extraction is provided to tap off at least a portion of the oxygen containing gas downstream of said compressor and upstream of said combustor, and wherein said extraction is part of a bypass, wherein said bypass bypasses said combustor and joins into a hot gas path downstream said combustor,
wherein said extraction comprises a valve to control the portion of the oxygen containing gas to be tapped off, said method comprising:
monitoring combustion gas temperatures via respective temperature measurements taken at different locations at respectively equal axial flow-distances downstream of the at least two burners of the combustion gas,
comparing two temperatures of said temperature measurements,
opening said valve or increasing an opening position of said valve when said comparison reveals that a difference between said two temperatures of said temperature measurements exceeds a temperature difference threshold.
2. The method according to claim 1 ,
wherein said oxygen containing gas is air.
3. The method according to claim 1 ,
wherein said at least one main combustion chamber is an annular combustion chamber.
4. The method according to claim 1 ,
wherein the number of burners of the at least two burners is between 4 and 24.
5. The method according to claim 1 ,
wherein the number of burners of the at least two burners is between 10 and 20.
6. The method according to claim 1 ,
wherein said fuel is a gas.
7. The method according to claim 1 ,
wherein said temperature measurements are located in one axial plane of said gas turbine engine, wherein a reference axis of the axial plane is a machine axis X of said gas turbine engine and an axis of rotation of at least one rotor of said gas turbine engine.
8. The method according to claim 1 , further comprising
decreasing the opening of said valve or closing said valve after a predetermined time of opening said valve or of increasing the opening position of said valve respectively.
9. The method according to claim 8 , wherein said predetermined time of opening is between 5 seconds and 180 seconds.
10. The method according to claim 8 , wherein said predetermined time of opening is between 10 seconds and 60 seconds.