Patent ID: 8381531

Claim:
A fuel injector for a gas turbine engine comprising: a pilot assembly extending along a longitudinal axis, the pilot assembly having a central passage configured to receive fuel and an outer passage configured to receive air, the pilot assembly being configured to direct a pilot fuel-air mixture to a combustor of the gas turbine engine; a rich catalyst module disposed within a housing and circumferentially disposed about the pilot assembly, the catalyst module configured to simultaneously direct a stream of compressed air and a stream of first fuel-air mixture therethrough without intermixing; a shroud positioned over the housing and defining an inlet opening; a fuel line connected to the shroud to supply a fuel through a fuel injection orifice disposed within the shroud to the catalyst module; a post mix zone disposed downstream of the catalyst module, the post mix zone configured to mix the compressed air and the first fuel air mixture to create a main fuel-air mixture; an air swirler disposed downstream of the post mix zone, the air swirler being configured to direct the main fuel-air mixture to the combustor without intermixing with the pilot fuel-air mixture; and a secondary mixing zone disposed downstream of the swirler.