Jet engine with toroidal air stream combustion

1. A jet engine system comprising:

a body having a longitudinal axis;

an air intake duct routing a first air stream along the longitudinal axis;

a combustion chamber having a central air inlet disposed at a proximal location, an inner casing defining an enclosed volume, an outer casing, and a diverter disposed within the enclosed volume at a distal location, the inner casing and the outer casing forming a casing gap channel around the inner casing, the inner casing having a set of air inlets arranged in radial patterns around the inner casing and passing through the inner casing, the enclosed volume having a throat disposed at a medial location;

a set of fuel lines in fluid communication with the enclosed volume and disposed within the casing gap channel, the set of fuel lines containing a fuel;

a rotational electric motor disposed distal to the combustion chamber and coupled to the set of fuel lines, the rotational electric motor providing power to supply the fuel contained in the fuel lines to the enclosed volume;

wherein:

the first air stream forms: i) a longitudinal air stream entering the combustion chamber through the central inlet and ii) a casing gap air stream entering the enclosed volume through the set of air inlets, the longitudinal air stream and the casing gap air stream forming a toroidal air stream within the enclosed volume;

the toroidal air stream mixes in the combustion chamber with the fuel and combusts when ignited within the enclosed volume to create an exhaust stream;

the exhaust stream exits through a thrust nozzle; and

thrust is produced.

2. The system of claim 1 , wherein the fuel is a hydrocarbon and the first air stream enters the combustion chamber in a pre-cracked state.

3. The system of claim 1 , wherein the first air stream is supplied by a compressor, the compressor disposed externally to the combustion chamber.

4. The system of claim 1 , wherein the throat forms a reduced diameter within the combustion chamber.

5. The system of claim 1 , wherein the set of air inlets are positioned upstream of the throat.

6. The system of claim 1 , further comprising a system controller that controls the rotational electric motor and controls at least one of a flow rate and a flow pressure of the fuel within the set of fuel lines.

7. The system of claim 1 , wherein the set of air inlets comprise a first set of air inlets positioned at a first axial location along the longitudinal axis and a second set of air inlets positioned at a second axial location along the longitudinal axis.

8. The system of claim 7 , wherein: at least one of the first set of air inlets and the second set of air inlets comprise teardrop-shaped air inlets, and at least one of the first set of air inlets and the second set of air inlets comprise circularly-shaped air inlets.

9. The system of claim 1 , wherein the fuel is a carbon negative fuel.

10. The system of claim 1 , wherein the combustion chamber further comprises a set of fuel flow guides operating to direct the fuel into the combustion chamber.

11. A method of using a jet engine system to produce thrust, the method comprising:

providing a jet engine system comprising:

a body having a longitudinal axis;

an air intake duct;

a combustion chamber having a central air inlet disposed at a proximal location, an inner casing defining an enclosed volume, an outer casing, and a diverter disposed at a distal location, the inner casing and the outer casing forming a casing gap channel around the inner casing, the inner casing having a set of air inlets arranged in radial patterns around the inner casing and passing through the inner casing, the enclosed volume having a throat disposed at a medial location;

a set of fuel lines in fluid communication with the enclosed volume and disposed within the casing gap channel, the set of fuel lines containing a fuel; and

a rotational electric motor disposed distal to the combustion chamber and coupled to the set of fuel lines;

receiving a first air stream;

forming a longitudinal air stream and a casing gap air stream from the first air stream;

flowing the longitudinal air stream into the enclosed volume;

flowing the casing gap air stream into the casing gap channel and into the enclosed volume through the set of air inlets;

forming a toroidal air stream within the enclosed volume;

supplying fuel to the enclosed volume using power supplied by the rotational electric motor;

mixing the toroidal air stream with the fuel to form a mixed fuel and air stream;

combusting the mixed fuel and air stream to form a combustion exhaust stream;

exiting the exhaust stream through a thrust nozzle;

wherein:

thrust is produced.

12. The method of claim 11 , wherein the fuel is a hydrocarbon.

13. The method of claim 12 , wherein the fuel undergoes heating during flow within the set of fuel lines.

14. The method of claim 11 , wherein the fuel enters the combustion chamber in a pre-cracked state.

15. The method of claim 11 , wherein the throat forms a reduced diameter within the combustion chamber.

16. The method of claim 15 , wherein the combustion exhaust stream accelerates when flowing through the throat.

17. The method of claim 11 , further comprising a system controller that controls the rotational electric motor and controls at least one of a flow rate and a flow pressure of the fuel within the set of fuel lines.

18. The method of claim 11 , wherein the set of air inlets comprise a first set of air inlets positioned at a first axial location along the longitudinal axis and a second set of air inlets positioned at a second axial location along the longitudinal axis.

19. The method of claim 11 , wherein the fuel is a carbon negative fuel.

20. The method of claim 18 , wherein each of the first set of air inlets and the second set of air inlets comprise at least one of circularly-shaped air inlets and teardrop shaped air inlets.