A gas turbine engine comprising: a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section comprising: 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), wherein the dome wall (90, 190, 290, 390, 490, 590, 690, 790) defines a conic portion (114a, 114b) forming an obtuse angle (β) with the combustor liner (82, 182, 282, 382, 482, 582); a fuel injector fluidly coupled to the dome inlet (96, 196, 496, 596, 696, 796); a combustion chamber fluidly coupled to the fuel injector 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, the at least one set of dilution openings (92, 93, 94, 192a, 192b, 193a, 193b, 292, 392, 492a, 492b) circumferentially arranged about the engine centerline; wherein the dome wall (90, 190, 290, 390, 490, 590, 690, 790) extends radially between the fuel injector and the combustor liner (82, 182, 282, 382, 482, 582) to define a flat portion (116, 116a, 116b), the flat portion (116, 116a, 116b) and the conic portion (114, 114a, 114b) meeting at a first junction; characterized in that the gas turbine engine further comprises a flare cone disposed around the fuel injector, the flare cone meeting the flat portion (116, 116a, 116b) at a second junction and wherein the flat portion (116, 116a, 116b) extends between the first junction and the second junction. 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), wherein the dome wall (90, 190, 290, 390, 490, 590, 690, 790) defines a conic portion (114a, 114b) forming an obtuse angle (β) with the combustor liner (82, 182, 282, 382, 482, 582); a fuel injector fluidly coupled to the dome inlet (96, 196, 496, 596, 696, 796); a combustion chamber fluidly coupled to the fuel injector 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, the at least one set of dilution openings (92, 93, 94, 192a, 192b, 193a, 193b, 292, 392, 492a, 492b) circumferentially arranged about the engine centerline; wherein the dome wall (90, 190, 290, 390, 490, 590, 690, 790) extends radially between the fuel injector and the combustor liner (82, 182, 282, 382, 482, 582) to define a flat portion (116, 116a, 116b), the flat portion (116, 116a, 116b) and the conic portion (114, 114a, 114b) meeting at a first junction; characterized in that the gas turbine engine further comprises a flare cone disposed around the fuel injector, the flare cone meeting the flat portion (116, 116a, 116b) at a second junction and wherein the flat portion (116, 116a, 116b) extends between the first junction and the second junction.