GAS TURBINE ENGINE WITH 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 (14) having a combustor liner (82, 182, 282, 382, 482, 582), a dome wall (90, 190, 290, 390, 490, 590, 690, 790) coupled to the combustor liner (82, 182, 282, 382, 482, 582), and a dome inlet (96, 196, 496, 596, 696, 796) located in the dome wall (90, 190, 290, 390, 490, 590, 690, 790), a fuel injector (76) fluidly coupled to the dome inlet (96, 196, 496, 596, 696, 796), a combustion chamber (86) fluidly coupled to the fuel injector (76) and defined at least in part by the combustor liner (82, 182, 282, 382, 482, 582) and the dome wall (90, 190, 290, 390, 490, 590, 690, 790), and at least one set of dilution openings (92, 93, 94, 192a, 192b, 193a, 193b, 292, 392, 492a, 492b) located in the dome wall (90, 190, 290, 390, 490, 590, 690, 790) and fluidly coupled to the combustion chamber (86).