| CPC F23R 3/10 (2013.01) [F23D 7/00 (2013.01); F23D 11/005 (2013.01); F23D 14/64 (2013.01); F23R 3/045 (2013.01); F23R 3/06 (2013.01); F23R 3/12 (2013.01); F23R 3/16 (2013.01); F23R 3/28 (2013.01); F23R 3/286 (2013.01); F23R 3/30 (2013.01); F23R 3/32 (2013.01)] | 20 Claims | 

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               1. A combustor system for an aerial vehicle, the combustor system comprising: 
            an outer case, the outer case extending from a first end to 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 first lumen into the central combustor chamber; 
                a first air flow path situated between and defined by the outer case and the inner combustor case; 
                a first integrated air scoop attached to the inner combustor case at the first lumen and configured to direct air from the first air flow path into the central combustor chamber; 
                a wedge within the first 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 with a fuel orifice within the first integrated air scoop; and 
                a splash plate comprising a first face and a second face, the splash plate extending through the first lumen into the central combustor chamber, 
                wherein the first integrated scoop and the second integrated scoop are configured to interlock and seal by pushing the wedge into the bifurcated orifice. 
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