Mesh based fuel flow guide
A combustor system for an aerial vehicle includes an outer liner with a first end and a second end, an inner combustor case within the outer liner, defining an outer periphery of a central combustor chamber, and having a lumen extending into the central combustor chamber. The system includes an air flow path extending between the outer liner and the inner combustor case, an integrated air scoop which directs air from the air flow path into the central combustor chamber, a fuel manifold with a fuel orifice within the integrated air scoop, and a lattice splash plate with a first face, second face, first end, and a second end. The lattice splash plate extends through the first lumen into the central combustor chamber, and includes lattice holes which are graded into the lattice splash plate from the first end to the second end of the lattice splash plate.
1 . A combustor system for an aerial vehicle, the combustor system comprising:
an outer liner, the outer liner having a first end and a second end;
an inner combustor case contained within the outer liner, the inner combustor case defining an outer periphery of a central combustor chamber, the inner combustor case having a first lumen extending into the central combustor chamber;
a first air flow path extending between and defined by the outer liner and the inner combustor case;
an 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 fuel manifold with a fuel orifice within the integrated air scoop; and
a lattice splash plate comprising a first face and a second face with a first end and a second end, the lattice splash plate extending through the first lumen into the central combustor chamber, wherein a plurality of lattice holes are graded into the lattice splash plate from the first end of the lattice splash plate to the second end of the lattice splash plate, wherein the lattice splash plate is curved and configured to direct air flow into the central combustor chamber, and wherein the lattice splash plate extends from within the first air flow path, through the first lumen, and into the central combustor chamber.
2 . The combustor system of claim 1 , wherein the lattice splash plate is connected to the integrated air scoop.
3 . The combustor system of claim 1 , wherein the integrated air scoop is canted and further comprises: a first end of the integrated air scoop connected to the inner combustor case on a first lip of the first lumen; and a second end of the integrated air scoop connected to the inner combustor case on a second lip of the first lumen.
4 . The combustor system of claim 3 , wherein the lattice splash plate is parallel to the second end of the integrated air scoop.
5 . The combustor system of claim 4 , wherein the fuel orifice is configured to direct fuel perpendicular to the second face of the lattice splash plate.
6 . The combustor system of claim 1 , wherein the fuel orifice is configured to direct fuel perpendicular to the second face of the lattice splash plate.
7 . The combustor system of claim 1 , wherein the lattice splash plate is spaced between a lip of the first lumen and an inner face of the integrated air scoop such that air from the first air flow path is split on the first face and the second face of the lattice splash plate.
8 . The combustor system of claim 1 , wherein the fuel orifice is located on an inner face of the integrated air scoop, and directs fuel perpendicular to and into the lattice holes of the lattice splash plate.
9 . The combustor system of claim 1 , wherein the fuel orifice is located on an inner face of the integrated air scoop.
10 . The combustor system of claim 1 , wherein the lattice splash plate is connected to a support member, the support member connected to the integrated air scoop.
11 . A combustor system for an aerial vehicle, the combustor system comprising:
an outer liner, the outer liner having a first end and a second end;
an inner combustor case contained within the outer liner, the inner combustor case defining an outer periphery of a central combustor chamber, the inner combustor case having a plurality of lumens extending through the inner combustor case into the central combustor chamber;
a first air flow path extending between and defined by the outer liner and the inner combustor case, and fluidly connected to the central combustor chamber by the plurality of lumens;
a plurality of 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 fuel manifolds with a plurality of fuel orifices within each respective integrated air scoop; and
a plurality of lattice splash plates comprising a first face and a second face, each respective splash plate extending through each respective lumen into the central combustor chamber, wherein a plurality of respective lattice holes are graded into the respective lattice splash plate from the first end of the respective lattice splash plate to the second end of the respective lattice splash plate, wherein at least one lattice splash plate of the plurality of lattice splash plates extends from within the first air flow path, through a respective lumen, and into the central combustor chamber.
12 . The combustor system of claim 11 , wherein each respective lattice splash plate is connected to the respective integrated air scoop.
13 . The combustor system of claim 11 , wherein at least one lattice splash plate of the plurality of lattice splash plates is curved and configured to direct air flow into the central combustor chamber.
14 . The combustor system of claim 11 , wherein at least one integrated air scoop of the plurality of integrated air scoops is canted with a first end of the integrated air scoop connected to the inner combustor case on a first lip of the respective lumen, and a second end of the integrated air scoop connected to the inner combustor case on a second lip of the respective lumen.
15 . The combustor system of claim 14 , wherein each respective lattice splash plate is parallel to the second end of the at least one integrated air scoop.
16 . The combustor system of claim 15 , wherein at least one fuel orifice of the plurality of fuel orifices is configured to direct fuel perpendicular to the respective second face of the respective lattice splash plate.