Abstract: A combustor liner for a gas turbine engine is disposed about an axis and defines a combustion chamber. The combustor liner includes a plurality of attachment elements circumferentially spaced about an outer wall of the combustor liner opposite the combustion chamber and a plurality of support elements connecting the plurality of attachment elements to combustor liner such that the plurality of attachment elements is radially spaced from the outer wall of the combustor liner. Each of the plurality of attachment elements includes an opening configured to slidingly receive a pin.

Abstract: A combustor system for an aerial vehicle can include an outer case with a first and second end, an inner combustor case with a lumen, a central combustor chamber, an air flow path between the outer case and inner combustor case, an integrated air scoop attached to the inner combustor case at the lumen that directs air from the air flow path into the central combustor chamber, a wedge within the integrated air scoop, a second integrated air scoop attached to the outer case, a bifurcated orifice integrated into the second integrated air scoop, a fuel manifold and fuel orifice within the first integrated air scoop, and a splash plate with a first and second face, the splash plate extending through the lumen into the central combustor chamber. The first and second integrated scoops can interlock and seal by pushing the wedge into the bifurcated orifice.