Patent ID: 7127897

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; and at least one combustion fluid injector disposed in a peripheral region of the plenum, the at least one combustion fluid injector 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 at least one combustion fluid injector 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 combustion chamber comprises at least two combustion fluid injectors, wherein the at least two combustion fluid injectors comprise at least one oxidant injector and at least one fuel injector, the combustion chamber being adapted to operate with separate oxidant and fuel injection.