Combustor mixing assembly

A combustor for a gas turbine engine, comprising:

• an annular inner liner having an inner liner upstream end and an inner liner downstream end;
• an annular outer liner spaced apart from the annular inner liner and having an outer liner upstream end and an outer liner downstream end;
• and
• a mixing assembly disposed at the inner liner upstream end and the outer liner upstream end, the mixing assembly comprising:
• a pilot mixer including an annular pilot housing having a hollow interior extending along a mixer centerline, and a pilot fuel nozzle mounted in the pilot housing;
• and
• a main mixer including:
• a main housing surrounding the pilot mixer, the main housing having a forward end and an aft end;
• a fuel manifold positioned between the pilot housing and the main housing;
• a mixer foot extending outward from the forward end of the main housing;
• a main swirler body including a plurality of vanes, the main swirler body surrounding the main housing such that an annular mixing channel is defined between the main housing and the main swirler body, and being coupled to the mixer foot;
• and
• an annular main fuel ring extending axially aft from the mixer foot into the annular mixing channel, wherein the mixer foot extends farther from the main housing than the main fuel ring,
• wherein at least one of the mixer foot or the main fuel ring includes a plurality of fuel injection ports positioned to discharge fuel into a central portion of the annular mixing channel.