BIMODAL SWIRLER INJECTOR FOR A GAS TURBINE COMBUSTOR

摘要

An improved air swirler and fuel injector for a gas turbine combustor system employs primary fuel injection into a primary recirculation combustion zone supplied by an inner annulus of swirling air at high fuel-air ratio under low power conditions. A selectively staged secondary fuel flow is supplied into an outer annulus downstream of secondary air swirlers supplying a secondary recirculation zone for combustion at higher fuel flows but lower fuel-air ratios under high power conditions. The secondary fuel flow may be separately injected into the outer annulus through conduit means extending through the primary air swirler vanes. Alternatively, the secondary fuel flow may be combined with the primary fuel in the fuel injector body and the momentum due to mass flow used to inject the fuel into the outer annulus.