Turbine engine including a combustor

A turbine engine comprising:

• a combustor configured to receive compressed air and comprising:
• a combustion chamber including an outer liner and an inner liner, the combustion chamber defining a radial direction, an axial direction, and a circumferential direction;
• and
• an annular dome coupled to the outer liner and the inner liner at a forward end of the combustion chamber;
• a plurality of first mixing assemblies each having a pilot mixer and a first main mixer concentrically aligned with the pilot mixer and extending circumferentially about the pilot mixer, the plurality of first mixing assemblies disposed through the annular dome, the pilot mixer of each of the plurality of first mixing assemblies operably injecting a pilot fuel stream axially and a first portion of the compressed air to generate a pilot fuel-air mixture axially into a first combustion zone of the combustion chamber, and the first main mixer of each of the plurality of first mixing assemblies operably injecting a first main fuel stream radially outward into the first main mixer and a second portion of the compressed air radially inward into the first main mixer in a direction opposite the first main fuel stream to generate a first main mixer fuel-air mixture that is injected into the first combustion zone, wherein, the plurality of first mixing assemblies are sized such that the first portion of the compressed air is 7% to 20% of the compressed air provided to the combustor and the second portion of the compressed air is 30% to 60% of the compressed air provided to the combustor;
• and
• a plurality of second mixing assemblies each having a second main mixer, the plurality of second mixing assemblies disposed through at least one of the outer liner or the inner liner axially aft of the plurality of first mixing assemblies, the second main mixer of each of the plurality of second mixing assemblies operably injecting a second main fuel stream and a third portion of the compressed air to generate a second main mixer fuel-air mixture radially into a second combustion zone of the combustion chamber, the second combustion zone being axially aft of, and separate from, the first combustion zone, and wherein, the plurality of second mixing assemblies are sized such that the third portion of the compressed air is 11% to 30% of the compressed air provided to the combustor.