Abstract: One embodiment of the present invention is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and components thereof. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A fuel nozzle for a gas turbine engine is provided having swirlers and a mounting device configured to mount the fuel nozzle to the inside of a combustor. In one embodiment the combustor has an interior surface formed to receive the mounting device of the fuel nozzle from within the combustor. The swirlers can be integrally formed in the fuel nozzle or can be separately attached, thus allowing the fuel nozzle to be mounted within the combustor having the relative placement of the swirlers already determined prior to installation. The fuel nozzle tip can be positioned a predetermined distance from the outlet of a swirler to reduce NOx emissions.