Dual pressure fuel nozzles

A fuel supply system for a gas turbine engine, comprising:

• a fuel nozzle having:
• a fuel swirler disposed inside a housing interior chamber, the fuel swirler having a fuel swirler upstream end and a fuel swirler downstream end relative to a fuel flow direction along a central longitudinal axis of the fuel nozzle, the fuel swirler including an end face at the fuel swirler downstream end, the end face disposed at a furthest downstream axial position of the fuel swirler relative to the central longitudinal axis;
• a first axial fuel passage radially formed between an inner fuel swirler and an outer fuel swirler relative to the central longitudinal axis, the first axial fuel passage in fluid communication with a hydrogen fuel supply in a housing having the housing interior chamber and terminating at a first fuel outlet at the fuel swirler downstream end, the first fuel outlet positioned on the end face, the end face bordering a mixing site downstream of and outside of the fuel swirler relative to the central longitudinal axis, and delivering hydrogen fuel directly to the mixing site;
• a second axial fuel passage radially formed between a swirler core and the inner fuel swirler relative to the central longitudinal axis, the second axial fuel passage in fluid communication with a liquid fuel supply in the housing and terminating at a second fuel outlet at the fuel swirler downstream end;
• wherein the first axial fuel passage and the second axial fuel passage are formed on opposite sides of an annular wall forming the inner fuel swirler, a first radial surface of the annular wall partially defining the first axial fuel passage and a second radial surface of the annular wall partially defining the second axial fuel passage;
• a first supply of compressed air through a plurality of end face compressed air outlets extending through the end face and circumferentially disposed relative to the central longitudinal axis about the end face;
• and
• a second supply of compressed air through an internal bore of the swirler core terminating at a swirler core compressed air outlet at the fuel swirler downstream end.