Patent ID: 7318317

Claim:
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.