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A fuel injector for a gas turbine engine may include a pilot assembly extending along a longitudinal axis. The pilot assembly may be configured to direct a pilot fuel-air mixture to a combustor of the gas turbine engine. The fuel injector may also include a rich catalyst module circumferentially dis

A fuel injector for a gas turbine engine may include a pilot assembly extending along a longitudinal axis. The pilot assembly may be configured to direct a pilot fuel-air mixture to a combustor of the gas turbine engine. The fuel injector may also include a rich catalyst module circumferentially disposed about the pilot assembly. The catalyst module may be configured to simultaneously direct a stream of compressed air and a stream of first fuel-air mixture therethrough without intermixing. The fuel injector may also include a post mix zone disposed downstream of the catalyst module. The post mix zone may be configured to mix the compressed air and the first fuel air mixture to create a main fuel-air mixture. The fuel injector may further include an air swirler disposed downstream of the post mix zone. The air swirler may be configured to direct the main fuel-air mixture to the combustor without intermixing with the pilot fuel-air mixture.

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1. 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

1. 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; anda secondary mixing zone disposed downstream of the swirler. 2. The fuel injector of claim 1, wherein an equivalence ratio of the first fuel-air mixture is above one and an equivalence ratio of the main fuel-air mixture is below one. 3. The fuel injector of claim 1, wherein the main fuel-air mixture enters the combustor circumferentially about the pilot fuel-air mixture. 4. The fuel injector of claim 1, wherein the catalyst module includes multiple hollow tubes extending along the longitudinal axis bundled together inside the housing. 5. The fuel injector of claim 4, wherein the stream of compressed air is directed through the multiple hollow tubes and the stream of first fuel-air mixture is directed through a space between the housing and an external surface of the multiple hollow tubes. 6. The fuel injector of claim 5, wherein the external surface is coated with a catalyst material. 7. The fuel injector of claim 1, wherein the post mix zone has a length between about 0.8 inches and about 2 inches. 8. The fuel injector of claim 1, wherein the secondary mixing zone has a length between about 0.5 inches and about 4 inches. 9. A fuel injector for a gas turbine engine, comprising: a center body having a central passageway to receive pilot fuel and an outer passage to receive air, the center body being configured to direct a stream of pilot fuel-air mixture to a combustor of the gas turbine engine,an annular outer passageway positioned circumferentially about the center body, the outer passageway configured to direct a stream of lean fuel-air mixture to the combustor without mixing with the pilot fuel-air mixture;a catalyst module positioned in the outer passageway, the catalyst module disposed within a housing and configured to simultaneously direct a stream of compressed air and a stream of rich 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 fuel through a fuel injection orifice disposed within the shroud to the catalyst module;a post mix zone positioned downstream of the catalyst module to mix the compressed air and the rich fuel-air mixture to create the lean fuel-air mixture;an air swirler positioned downstream of the post mix zone; anda secondary mixing zone disposed downstream of the swirler. 10. The fuel injector of claim 9, wherein an equivalence ratio of the pilot fuel-air mixture is above one and an equivalence ratio of the lean fuel-air mixture is below one. 11. The fuel injector of claim 9, wherein the lean fuel-air mixture enters the combustor circumferentially about the pilot fuel-air mixture. 12. The fuel injector of claim 9, wherein the catalyst module includes multiple hollow tubes extending along the longitudinal axis bundled together inside the housing. 13. The fuel injector of claim 9, wherein the post mix zone has a length between about 0.8 inches and about 2 inches. 14. The fuel injector of claim 9, wherein the secondary mixing zone has a length between about 0.5 inches and about 4 inches.