Combustion chamber and method for operating a combustion chamber
View Patent ↗A combustion chamber of a gas turbine including first and second premixed fuel supply devices connected to a combustion device having first zones connected to the first premixed fuel supply devices and second zones connected to the second premixed fuel supply devices. The second fuel supply devices are shifted along a combustion device longitudinal axis with respect to the first fuel supply devices. The first zones are axially upstream of the second premixed fuel supply devices.
1. A combustion chamber, of a gas turbine, comprising:
a plurality of first and second premixed fuel supply devices arranged in a first circumferential row, each of the plurality of first premixed fuel supply devices having a first longitudinal axis, each of the second premixed fuel supply devices having a second longitudinal axis, each of the first longitudinal axes and the second longitudinal axes of the first and second premixed fuel supply devices arranged at a same radial position from a central longitudinal axis, and wherein each of the first longitudinal axes and the second longitudinal axes of the first and second premixed fuel supply devices is parallel to one another, each first fuel premixed fuel supply device being adjacent to at least two second premixed fuel supply devices, and each of the plurality of first and second premixed fuel supply devices having a conical shape with tangential slots for air entrance within the first and second premixed fuel supply devices and nozzles close to the tangential slots for fuel injection, the first and second premixed fuel supply devices connected to a combustion device having first zones connected to the first premixed fuel supply devices and second zones connected to the second premixed fuel supply devices, wherein the second fuel supply devices are shifted along the central longitudinal axis with respect to the first fuel supply devices, the first zones are axially upstream of the second premixed fuel supply devices; and
wherein flames generated in the first and second zones of the first and second premixed fuel supply devices are in the first and second zones, respectively, and the flames generated by the first premixed fuel supply devices are housed axially upstream of the second premixed fuel supply devices.
2. The combustion chamber as claimed in claim 1 , wherein the first and second premixed fuel supply devices have different circumferential positions.
3. The combustion chamber as claimed in claim 1 , wherein the first longitudinal axes of the first premixed fuel supply devices and the second longitudinal axes of the second fuel supply devices are also parallel to the central longitudinal axis.
4. The combustion chamber as claimed in claim 1 , wherein the first and second premixed fuel supply devices inject a mixture along their parallel first and second longitudinal axes.
5. A method of operating a combustion chamber of a gas turbine having a plurality of first and second premixed fuel supply devices arranged in a first circumferential row, each of the plurality of first premixed fuel supply devices having a first longitudinal axis, each of the second premixed fuel supply devices having a second longitudinal axis, each of the first longitudinal axes and the second longitudinal axes of the first and second premixed fuel supply devices arranged at a same radial position from a central longitudinal axis, and wherein each of the first longitudinal axes and the second longitudinal axes of the first and second premixed fuel supply devices is parallel to one another, each first fuel premixed fuel supply device being adjacent to at least two second premixed fuel supply devices, and each of the plurality of first and second premixed fuel supply devices having a conical shape with tangential slots for air entrance within the first and second premixed fuel supply devices and nozzles close to the tangential slots for fuel injection, the first and second premixed fuel supply devices connected to a combustion device that has first zones connected to the first premixed fuel supply devices and second zones connected to the second premixed fuel supply devices, the method comprising:
arranging the second premixed fuel supply devices along the central longitudinal axis with respect to the first premixed fuel supply devices;
arranging the first zones axially upstream of the second premixed fuel supply devices; and
feeding a fuel and an oxidizer into the first and second premixed fuel supply devices to generate a mixture that is burnt within the combustion device, and wherein flames generated in the first and second zones of the first and second premixed fuel supply devices are in the first and second zones, respectively, and the flames generated by the first premixed fuel supply devices are housed axially upstream of the second premixed fuel supply devices.
6. The method according to claim 5 , wherein the first fuel supply devices and the second fuel supply devices generate flames having different temperatures.
7. The method according to claim 5 , wherein the flames generated by the first premixed fuel supply devices have a higher temperature than the flames generated by the second premixed fuel supply devices.
8. The method according to claim 7 , wherein at part load, fuel supplied into the second premixed fuel supply devices is reduced, but fuel supplied into the first premixed fuel supply devices is maintained constant.
9. The method according to claim 7 , wherein at low load the second premixed fuel supply devices are switched off and only the first premixed fuel supply devices are operated.
10. The method according to claim 7 , wherein at part load the second premixed fuel supply devices are operated generating flames with temperature above a limit compatible with pulsation but below a limit compatible with CO emissions.
11. The method according to claim 7 , wherein at high part load the first and second premixed fuel supply devices are operated generating flames with flame temperatures astride of a required flame temperature.
12. The combustion chamber as claimed in claim 1 , wherein the fuel injected through the nozzles is a gaseous fuel.
13. The combustion chamber as claimed in claim 1 , comprising:
lances extending axially within the first and second premixed fuel supply devices for injecting a liquid fuel.
14. The method according to claim 5 , wherein the fuel injected through the nozzles is a gaseous fuel.
15. The method according to claim 5 , comprising:
injecting a liquid fuel through lances extending axially within the first and second premixed fuel supply devices.
16. The combustion chamber as claimed in claim 1 ,
further comprising a second circumferential row of the plurality of first and second premixed fuel supply devices.
17. The method according to claim 5 ,
further comprising a second circumferential row of the plurality of first and second premixed fuel supply devices.