Integrated additive fuel injectors for attritable engines
An attritable engine includes an engine case, which includes an outer wall and a fuel rail integral with the outer wall. The fuel rail includes a fuel line integral with the outer wall, a fuel ring configured to receive fuel from the fuel line, and an injector throat configured to receive aerated fuel from the fuel ring. The engine case includes counter distortion webbing defining the injector throat and is integral with the fuel rail and the outer wall. The engine case includes a combustion chamber configured to receive fuel from the injector throat.
1. An assembly for an engine, comprising:
a liner extending circumferentially about an axis, a combustion chamber formed by and radially within a radial inner liner surface of the liner;
an outer wall extending circumferentially about and spaced radially from the liner;
a fuel line extending circumferentially within the outer wall;
an injector throat fluidly coupled with the fuel line, the injector throat angularly offset from a radial inner wall surface of the outer wall by an acute angle in a radial plane with respect to the axis, the injector throat further angularly offset from the radial inner liner surface by the acute angle in the radial plane, the radial plane parallel with the axis, and the injector throat configured to direct fuel received from the fuel line into the combustion chamber through a throat outlet;
a webbing projecting radially inward from the outer wall towards the liner, the webbing forming the injector throat, and the webbing configured with a triangular cross-sectional geometry in the radial plane;
a compressor rotor comprising a plurality of compressor blades, the compressor rotor rotatable about the axis; and
a turbine rotor comprising a plurality of turbine blades, the turbine rotor rotatable about the axis and disposed axially between the compressor rotor and the injector throat along the axis;
wherein the triangular cross-sectional geometry has a first side, a second side and a third side;
the first side is at the outer wall and extends along the axis;
the second side is adjacent and extends parallel to the injector throat;
the third side forms a distal side of the webbing exposed to a plenum radially between the outer wall and the liner; and
the throat outlet is located on the third side and faces an opening in the liner, and the throat outlet is configured to inject the fuel into the plenum.
2. The assembly of claim 1 , wherein the outer wall, the fuel line, the injector throat and the webbing are collectively formed by a monolithic body.
3. The assembly of claim 1 , wherein the injector throat extends to the throat outlet in a direction along the axis towards the compressor rotor.
4. The assembly of claim 1 , further comprising:
an airflow inlet to the engine at a forward end of the engine along the axis; and
an exhaust outlet from the engine at an aft end of the engine along the axis;
the injector throat extending longitudinally to the throat outlet in a forward direction towards the forward end of the engine.
5. The assembly of claim 1 , wherein the liner extends circumferentially about the axis such that
a first portion of the liner is disposed to a first radial side of the axis; and
a second portion of the liner is disposed to a second radial side of the axis that is opposite the first radial side of the axis.
6. The assembly of claim 1 , wherein
a first portion of the combustion chamber is disposed to a first radial side of the axis; and
a second portion of the combustion chamber is disposed to a second radial side of the axis that is opposite the first radial side of the axis.
7. The assembly of claim 1 , wherein the fuel line is integral with the outer wall.
8. The assembly of claim 1 , further comprising a fuel rail integral with the outer wall, the fuel rail comprising:
the fuel line;
a fuel ring configured to receive the fuel from the fuel line; and
the injector throat configured to receive the fuel from the fuel ring.
9. The assembly of claim 8 , further comprising:
an access port disposed to a radial outer side of the outer wall;
the access port extending at an acute angle through the outer wall to the fuel ring.
10. An assembly for an engine, comprising:
a liner extending circumferentially about an axis, a combustion chamber formed by and radially within the liner, a first portion of the combustion chamber disposed to a first radial side of the axis, and a second portion of the combustion chamber disposed to a second radial side of the axis that is opposite the first radial side of the axis;
an outer wall extending circumferentially about and spaced radially from the liner;
a fuel line extending circumferentially within the outer wall;
an injector throat fluidly coupled with the fuel line, the injector throat angularly offset from a radial inner surface of the outer wall by an acute angle in a radial plane with respect to the axis, the injector throat configured to direct fuel received from the fuel line into the combustion chamber through a throat outlet;
a webbing projecting radially inward from the outer wall towards the liner, the webbing forming the injector throat, and the webbing configured with a triangular cross-sectional geometry in the radial plane; and
a compressor rotor comprising a plurality of compressor blades, the compressor rotor rotatable about the axis, wherein the injector throat extends to the throat outlet in a direction along the axis towards the compressor rotor;
wherein the triangular cross-sectional geometry has a first side, a second side and a third side;
the first side is at the outer wall and extends along the axis;
the second side is adjacent and extends parallel to the injector throat;
the third side forms a distal side of the webbing exposed to a plenum radially between the outer wall and the liner; and
the throat outlet is located on the third side and faces an opening in the liner, and the throat outlet is configured to inject the fuel into the opening in the liner through the plenum.