Combustion section with a primary combustor and a set of secondary combustors

A turbine engine comprising:

• a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline, the combustion section comprising:
• an inner liner circumferentially arranged about the engine centerline;
• an outer liner spaced radially outward from and concentric with the inner liner;
• a dome wall extending between the inner liner and the outer liner;
• a dome inlet located in the dome wall;
• a primary combustor having a primary combustion chamber defined at least in part by the inner liner, the outer liner, and the dome wall and extending between the dome inlet and a primary combustor outlet, wherein the primary combustor outlet is located a primary combustor length from the dome inlet, and wherein an upstream direction is defined from the primary combustor outlet to the dome inlet and a downstream direction from the dome inlet to the primary combustor outlet;
• at least one opening located in the outer liner downstream from the dome inlet, wherein the outer liner is free of dilution openings upstream of the at least one opening;
• and
• a set of secondary combustors including at least one secondary combustion chamber fluidly coupled to the primary combustion chamber at the at least one opening to define a secondary combustor outlet, the set of secondary combustors comprising a mini combustor and a mini fuel injector fluidly coupled to a secondary fuel passageway, wherein the mini fuel injector terminates at a mini dome inlet defining a secondary centerline directed toward the dome inlet;
• wherein secondary exhaust gasses G2 from the mini combustor are directed towards the primary combustion chamber, and wherein at least a portion of the secondary exhaust gasses G2 mix with primary exhaust gasses G1 upstream of the at least one opening.