Gas turbine with improved part load emissions behavior
View Patent ↗In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the opening of the row of variable compressor inlet guide vanes is controlled depending on the temperatures of the operative burners of the second combustor and simultaneously the number of operative burners is kept at a minimum. This leads to low CO emissions at partial load of the gas turbine.
1. A method for low-CO emissions operation of a gas turbine with sequential combustion, wherein the gas turbine includes a first turbine, a second turbine, at least one compressor wherein the at least one compressor includes a row of variable compressor inlet guide vanes, a first combustor which is connected downstream to the compressor and the hot gases of which are admitted to the first turbine, and a second combustor which is connected downstream to the first turbine and the hot gases of which are admitted to the second turbine, the second combustor including operative burners each having a burner exhaust temperature, the method comprising:
controlling a position of the variable compressor inlet guide vanes depending on a burner exhaust temperature of at least one the operative burners of the second combustor;
in case of increasing loads, switching “ON” a further operative burner of the second combustor in case an average of the turbine exhaust temperature of the second turbine reaches a lower limit value;
in case of decreasing loads switching “OFF” one of the operative burners of the second combustor in case the average of the turbine exhaust temperature of the second turbine reaches the lower limit value; and
at least one of:
controlling the position of the variable compressor inlet guide vanes depending on a difference between the highest burner exhaust temperature of the operative burners and a maximum turbine exhaust temperature;
opening the variable compressor inlet guide vanes when the burner exhaust temperature of one of the operative burners reaches or exceeds the maximum turbine exhaust temperature; and
closing the variable compressor inlet guide vanes when the highest burner exhaust temperature of the operative burners is below the maximum turbine exhaust temperature.
2. The method as claimed in claim 1 , wherein the opening of the variable compressor inlet guide vanes when the burner exhaust temperature of one of the operative burners reaches or exceeds a maximum turbine exhaust temperature is performed.
3. The method as claimed in claim 2 , wherein the position of the variable compressor inlet guide vanes is controlled depending on the maximum turbine exhaust temperature of the operative burners of the second combustor.
4. The method as claimed in claim 1 , wherein the closing of the variable compressor inlet guide vanes when the highest burner exhaust temperature of the operative burners is below a maximum turbine exhaust temperature is performed.
5. The method as claimed in claim 4 , wherein the position of the variable compressor inlet guide vanes is controlled depending on the maximum turbine exhaust temperature of the operative burners of the second combustor.
6. The method of claim 1 , comprising:
increasing a rate of fuel supplied to the second combustor and/or the first combustor with a load increase.
7. The method as claimed in claim 1 , comprising:
decreasing a rate of fuel supplied to the second combustor and/or the first combustor with a load decrease.
8. The method as claimed in claim 1 , wherein both of the opening of the variable compressor inlet guide vanes when the burner exhaust temperature of one of the operative burners reaches or exceeds a maximum turbine exhaust temperature and the closing of the variable compressor inlet guide vanes when the highest burner exhaust temperature of the operative burners is below the maximum turbine exhaust temperature are performed.
9. The method as claimed in claim 1 , wherein the
controlling of the position of the variable compressor inlet guide vanes depending on a difference between the highest burner exhaust temperature of the operative burners and the maximum turbine exhaust temperature is performed.
10. The method as claimed in claim 1 , wherein a control unit of the gas turbine performs the switching “ON” and performs the switching “OFF”.
11. The method as claimed in claim 1 , wherein the gas turbine comprises
at least one fuel line leading to the operative burners.
12. A method for low-CO emissions operation of a gas turbine with sequential combustion, wherein the gas turbine includes a first turbine, a second turbine, at least one compressor wherein the at least one compressor includes a row of variable compressor inlet guide vanes, a first combustor which is connected downstream to the compressor and the hot gases of which are admitted to the first turbine, and a second combustor which is connected downstream to the first turbine and the hot gases of which are admitted to the second turbine, the second combustor including operative burners each having a burner exhaust temperature, the method comprising:
controlling a position of the variable compressor inlet guide vanes depending on a burner exhaust temperature of at least one the operative burners of the second combustor;
in case of increasing loads, switching “ON” a further operative burner of the second combustor in case an average of the turbine exhaust temperature of the second turbine reaches a lower limit value;
in case of decreasing loads switching “OFF” one of the operative burners of the second combustor in case the average of the turbine exhaust temperature of the second turbine reaches the lower limit value; and
wherein in case all operative burners of the second combustor are in operation, controlling the position of the variable compressor inlet guide vanes depending on the average temperature of the turbine exhaust temperature.
13. The method as claimed claim 12 , wherein the position of the variable compressor inlet guide vanes is controlled so that the average temperature of the turbine exhaust temperature is equal to an upper limit of the average turbine exhaust temperature.
14. The method as claimed in claim 12 , further comprising:
increasing a rate of fuel supplied to the second combustor and/or the first combustor with a load increase.
15. The method as claimed in claim 12 , further comprising:
decreasing a rate of fuel supplied to the second combustor and/or the first combustor with a load decrease.
16. A gas turbine comprising:
a compressor with variable inlet guide vanes;
a first turbine;
a second turbine;
a first combustor connected downstream to the compressor such that during operation hot gases from the first combustor are admitted to the first turbine; and a second combustor connected downstream to the first turbine such that hot gases from the second combustor are admitted to the second turbine wherein the second combustor comprises a plurality of operative burners;
at least one fuel line leading to the plurality of operative burners of the second combustor; and
an individual on/off valve or an individual control valve arranged in at least one fuel line to control individual operative burners and a control unit, the control unit executing the method of claim 12 .
17. The method as recited in claim 12 , comprising at least one of:
opening the variable compressor inlet guide vanes when the burner exhaust temperature of one of the operative burners reaches or exceeds a maximum turbine exhaust temperature; and
closing the variable compressor inlet guide vanes when the highest burner exhaust temperature of the operative burners is below the maximum turbine exhaust temperature.
18. The method as recited in claim 12 , comprising both of:
opening the variable compressor inlet guide vanes when the burner exhaust temperature of one of the operative burners reaches or exceeds a maximum turbine exhaust temperature; and
closing the variable compressor inlet guide vanes when the highest burner exhaust temperature of the operative burners is below the maximum turbine exhaust temperature.
19. A method for low-CO emissions operation of a gas turbine with sequential combustion, wherein the gas turbine includes a first turbine, a second turbine, at least one compressor wherein the at least one compressor includes a row of variable compressor inlet guide vanes, a first combustor which is connected downstream to the compressor and the hot gases of which are admitted to the first turbine, and a second combustor which is connected downstream to the first turbine and the hot gases of which are admitted to the second turbine, the second combustor including operative burners each having a burner exhaust temperature, the method comprising:
controlling a position of the variable compressor inlet guide vanes depending on a burner exhaust temperature of at least one the operative burners of the second combustor;
in case of increasing loads, switching “ON” a further operative burner of the second combustor in case an average of the turbine exhaust temperature of the second turbine reaches a lower limit value;
in case of decreasing loads switching “OFF” one of the operative burners of the second combustor in case the average of the turbine exhaust temperature of the second turbine reaches the lower limit value; and
wherein an upper limit value of the average turbine exhaust temperature is greater than the lower limit value.
20. The method as claimed in claim 19 , wherein the position of the variable compressor inlet guide vanes is controlled depending on the maximum turbine exhaust temperature of the operative burners of the second combustor.