Unitary case integrated flow scoops

A combustor system for an aerial vehicle, the combustor system comprising:

• an outer case, the outer case having a first end and a second end;
• an inner combustor case contained within the outer case, the inner combustor case defining an outer periphery of a central combustor chamber, the inner combustor case having a plurality of lumens into the central combustor chamber;
• a first air flow path between the outer case and the inner combustor case;
• an plurality of inner integrated air scoops, each respective integrated air scoop attached to the inner combustor case at each respective lumen and configured to direct air from the first air flow path into the central combustor chamber;
• a plurality of wedges within each respective inner integrated air scoop;
• a bifurcated orifice integrated into the second integrated air scoop;
• an plurality of outer integrated air scoops, each respective integrated air scoop attached to the outer case and configured to interlock and seal with the plurality of inner integrated air scoops;
• a plurality of bifurcated orifices integrated into each respective outer integrated air scoop;
• a plurality of fuel manifolds with a plurality of fuel orifices within each respective inner integrated air scoop;
• and
• a plurality of splash plates comprising a first face and a second face, each respective splash plate extending through each respective lumen into the central combustor chamber;
• and
• wherein each respective inner integrated air scoop and each respective outer integrated air scoop are sealed against one another via each respective wedge and each respective bifurcated orifice.