GAS TURBINE ENGINE HAVING A DUAL OUTLET FUEL-PREMIX-NOZZLE FOR A SECONDARY COMBUSTOR STAGE

摘要

A secondary fuel stage (14) of a combustor of a gas turbine engine. The combustor has a main combustion zone upstream of the secondary fuel stage to ignite working gas. The secondary fuel stage includes a nozzle (18) with dual outlets (20, 22) oriented with a circumferential component to inject an air-fuel mixture into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas such that a peak temperature of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle.