Turbine engine combustor and combustor liner

A turbine engine, comprising:

• a compressor section, a combustion section, and a turbine section in serial flow arrangement, and the combustion section having a combustor defining a combustor axis and comprising:
• a combustor liner at least partially comprising a combustion chamber, the combustor liner defining an outer liner and an inner liner;
• a dome assembly coupled to the combustor liner and at least partially defining the combustion chamber;
• a compressed air passage fluidly coupling the compressor section to the combustion chamber;
• a first aperture extending through the combustor liner adjacent the dome assembly and fluidly coupling the compressed air passage to the combustion chamber;
• a second aperture extending through the combustor liner and axially spaced downstream from the first aperture along the combustor axis;
• a fence wall located downstream of the second aperture and projecting radially, with respect to the combustor axis, into the combustion chamber from the outer liner;
• and
• an additional fence wall located downstream of the second aperture and projecting radially, with respect to the combustor axis, into the combustion chamber from the inner liner, the fence wall and the additional fence wall axially aligned along the combustor axis;
• wherein each of the fence wall and the additional fence wall is configured to direct a fluid flow from at least one of the first aperture or the second aperture toward the center of the combustor to keep a combustion flame away from the combustor liner.