Gas turbine engine, fuel nozzle assembly, and method

A gas turbine engine, comprising:

• a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising:
• a combustor liner at least partially defining a combustion chamber;
• a wall coupled to the combustor liner;
• a first fuel supply to supply a first fuel;
• a gaseous fuel supply to supply a gaseous hydrogen fuel;
• and
• a fuel nozzle assembly coupled to the wall and fluidly coupled to the first fuel supply and the gaseous fuel supply, the fuel nozzle assembly comprising:
• a main mixer, the main mixer and the wall defining a cavity;
• and
• a fuel nozzle disposed such that the main mixer is disposed at least partially around the fuel nozzle, the fuel nozzle comprising:
• an outer wall defining a pilot channel;
• an outer wall fuel orifice extending through the outer wall and fluidly coupled with the first fuel supply and the gaseous fuel supply to emit at least one of the first fuel or the gaseous hydrogen fuel radially outward into the main mixer;
• a secondary mixer disposed in the pilot channel;
• and
• a first flame shaping aperture extending through the wall to emit air into the cavity, wherein the first flame shaping aperture is aft of the outer wall fuel orifice.

A gas turbine engine, comprising:

• a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising:
• a combustor liner at least partially defining a combustion chamber;
• a wall coupled to the combustor liner;
• a first fuel supply to supply a first fuel;
• a gaseous fuel supply to supply a gaseous hydrogen fuel;
• and
• a fuel nozzle assembly coupled to the wall and fluidly coupled to the first fuel supply and the gaseous fuel supply, the fuel nozzle assembly comprising:
• a main mixer;
• and
• a fuel nozzle disposed such that the main mixer is disposed at least partially around the fuel nozzle, the fuel nozzle comprising:
• an outer wall defining a pilot channel;
• an outer wall fuel orifice extending through the outer wall and fluidly coupled with the first fuel supply and the gaseous fuel supply to emit at least one of the first fuel or the gaseous hydrogen fuel radially outward into the main mixer;
• and
• a secondary mixer disposed in the pilot channel;
• wherein the wall includes a first flame shaping aperture aft of the outer wall fuel orifice and a second flame shaping aperture aft of the first flame shaping aperture, the second flame shaping aperture directed radially inward and aft of an outlet of the main mixer, the first flame shaping aperture positioned radially outward and forward of the outlet of the main mixer and the second flame shaping aperture positioned radially outward of the first flame shaping aperture;
• wherein the main mixer and the wall define a cavity;
• and
• wherein the first flame shaping aperture extends through the wall to emit air into the cavity.