Patent ID: 6539721
Filing Date: 2003-04-01
Classification: F23D,F23R

Abstract:
A mixer for a gas turbine combustor comprising:a chamber having a substantially truncated conical shape with an upstream end having a diameter smaller than a diameter of an open downstream end of the chamber; a truncated conical annulus having a diameter at a downstream end thereof, smaller than a diameter of an upstream end thereof, the annulus at the downstream end thereof communicating with the chamber at the upstream end thereof; a first fuel injection means disposed in the annulus for injecting gaseous fuel into the annulus; a plurality of upstream air passages communicating with the annulus, located upstream of the first fuel injection means for supplying air flow into the annulus to mix with the gaseous fuel injected into the annulus, thereby forming a fuel and air mixture; a plurality of downstream air passages communicating with the chamber, located adjacent to the upstream end of the chamber for introducing air flow, to further mix in the chamber with the fuel and air mixture; a central passage directly communicating with the chamber at a center of the upstream end thereof for supplying air flow into the chamber; and a second fuel injection means disposed adjacent to the upstream end of the chamber for injecting liquid fuel into the central passage to mix with air therein.