Fuel nozzle for a turbine having dual capability for diffusion and

Abstract

The fuel nozzle includes an annular chamber defined between a housing and a central tube. At the downstream end of the tube, inner and outer swirlers are provided in communication with the upstream chamber and a combustion zone downstream of the swirlers. When fuel gas is supplied the inner swirler, a portion of the air flowing through the chamber mixes in the inner swirler with the supplied fuel for holding a diffusion flame in a downstream diffusion mixing cup. The balance of the air flowing through the chamber through the outer swirler is segregated from the air supplied the inner swirler by a circumferentially extending splitter vane. At an upstream portion of the chamber a plurality of spokes pass into the chamber for supplying fuel gas to the chamber when the nozzle operates in a premix combustion mode. When operating in a premix combustion mode, fuel gas is cut off from the inner swirler and supplied to the spokes. The fuel and air are mixed in the chamber and pass through both the inner and outer swirlers, forming a premix flame front within a downstream premix cup in the combustion zone.