COMBUSTOR WITH DILUTION OPENINGS

A gas turbine engine (10) including a compressor section (12) and a combustion section (14) in serial flow arrangement along an engine centerline (21), the combustion section having an annular dome wall circumscribing the engine centerline; an annular combustor liner extending from the annular dome wall to define an annular combustion chamber in combination with the annular dome wall; first and second, concentrically arranged and radially spaced, annular dilution holes formed in the annular dome wall to define an annular space between the first and second annular dilution holes; and multiple fuel injectors circumferentially spaced about the annular space between the first and second annular dilution holes.