Patent ID: 6826912
Filing Date: 2004-12-07
Classification: F23C,F23R,Y02E

Abstract:
A system comprising:an adiabatic combustor for a gas turbine, said combustor including: a) a combustion chamber designed and configured to produce high-pressure combustion gases for said turbine, said combustion chamber having a primary combustion zone containing a substantially vitiated-air zone; b) at least one primary air inlet providing air to said primary combustion zone, and c) a fuel injector for injecting fuel, disposed such that said fuel is directly introduced to said vitiated-air zone, said primary air inlet being positioned and directed, and said combustion chamber being designed and configured, so as to produce an internal recirculation that generates a toroidal vortex within said primary combustion zone, thereby producing therein said vitiated-air zone and maintaining therein a state of flameless oxidation.