Combustion chamber for a gas turbine
View Patent ↗A combustion chamber 10 for a gas turbine that operates in a highly diluted mode of combustion has a substantially toroidal plenum 30 . At least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the disposition of the combustion fuel injectors are such that a vortex flow 2 is established in the combustion chamber in use. Gasses are entrained in the vortex which provides high enough levels of flue gas re-circulation to allow for the onset of highly diluted combustion.
1. A combustion chamber for a gas turbine, the combustion chamber comprising:
a substantially toroidal plenum extending around a rotor axis of the gas turbine, the plenum comprising a substantially tangential outlet that extends around a radially inner peripheral region of the plenum, wherein the tangential outlet is adapted to direct gases towards the turbine in a direction that is substantially parallel to the rotor axis of the turbine;
a plurality of combustion fluid injectors disposed in a peripheral region of the plenum, at least two injectors of the plurality of combustion fluid injectors positioned in the same radial section on one side of the rotor axis, the plurality of combustion fluid injectors being adapted to inject fluid into the plenum to establish a vortex flow in a central region of the plenum that extends around the rotor axis of the gas turbine in a circular path;
wherein the plurality of combustion fluid injectors is adapted to entrain sufficient gasses in the vortex to establish a high enough flue gas re-circulation rate to enable the generation of a highly diluted combustion mode in the plenum during combustion; and
wherein the injected fluid comprises an at least partially premixed mixture of fuel and oxidant.
2. A combustion chamber according to claim 1 , wherein an angle formed between a direction of fluid injection from each of the plurality of combustion fluid injectors and a tangential direction at a point where the fluid meets the vortex is from 0° to 90°.
3. A combustion chamber according to claim 2 , wherein the angle is from 15° to 60°.
4. A combustion chamber according to claim 1 , wherein each of the plurality of combustion fluid injectors has a swirl coefficient of less than 0.6.
5. A combustion chamber according to claim 1 , wherein each of the plurality of combustion fluid injectors has a swirl coefficient of less than 0.4.
6. A combustion chamber according claim 1 , wherein the substantially tangential outlet is adapted to extend around an entire radially inner peripheral region of the plenum to define a circular outlet.
7. A combustion chamber according to claim 1 , wherein the substantially tangential outlet comprises a nozzle.
8. A combustion chamber according to claim 1 , further comprising:
a guide device located either upstream or downstream of the substantially tangential outlet, the guide device being adapted to direct gasses into the blades of the turbine.
9. A combustion chamber according to claim 8 , wherein the guide device comprise a vane or a blade.