Gas turbine engine and fuel-air mixer thereof

A gas turbine engine, comprising:

• a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section comprising:
• a combustor liner that at least partially defines a combustion chamber;
• and
• a fuel-air mixer receiving fuel comprising at least 75% by mass diatomic hydrogen, the fuel-air mixer being fluidly coupled with the combustion chamber, the fuel-air mixer comprising:
• an outer wall;
• a center body disposed radially inward of the outer wall;
• a first splitter disposed at least partially between the outer wall and the center body, and including a first lobed trailing edge;
• a second splitter disposed at least partially between the first splitter and the outer wall, and including a second lobed trailing edge axially offset from the first lobed trailing edge, wherein the first lobed trailing edge is axially downstream of the second lobed trailing edge;
• a first swirler disposed at least partially between the first splitter and the second splitter;
• and
• a set of fuel orifices located at the first lobed trailing edge, the second lobed trailing edge, or the first lobed trailing edge and the second lobed trailing edge.