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

A combustion section for a turbine engine, the combustion section comprising:

• a primary combustor liner including an inner liner and an outer liner in annular arrangement about an engine centerline, the engine centerline defining an axial direction along the engine centerline, defining a radial direction extending perpendicular from the engine centerline, and defining a circumferential direction extending circumferentially about the engine centerline;
• a dome wall extending between the inner liner and the outer liner;
• a set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline;
• 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
• a secondary combustor fluidly coupled to the primary combustion chamber at the outer liner, wherein the secondary combustor is provided as a set of secondary combustors including at least a first mini combustor and a second mini combustor, wherein the first mini combustor and the second mini combustor are arranged to exhaust combustion products in the same circumferential direction;
• wherein the secondary combustor is turned, along the outer liner at an opening angle, relative to the axial direction, such that the secondary combustor generates combustion products that are injected into the primary combustion chamber circumferentially about the outer liner respective of the opening angle.