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A rocket engine includes a combustor assembly for carrying out a combustion process of fuel and oxidizer rocket propellants to produce thrust. A swirl generator is positioned within the combustor assembly to produce a turbulent flowfield of the fuel and oxidizer rocket propellants within the combust

A rocket engine includes a combustor assembly for carrying out a combustion process of fuel and oxidizer rocket propellants to produce thrust. A swirl generator is positioned within the combustor assembly to produce a turbulent flowfield of the fuel and oxidizer rocket propellants within the combustor assembly.

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The invention claimed is: 1. A rocket engine comprising: a combustor chamber; an inlet delivery duct coaxial with said combustion chamber; a plurality of liquid propellant injectors mounted to said inlet delivery duct; a swirl generator mounted to said inlet delivery duct, said swirl generator comp

The invention claimed is: 1. A rocket engine comprising: a combustor chamber; an inlet delivery duct coaxial with said combustion chamber; a plurality of liquid propellant injectors mounted to said inlet delivery duct; a swirl generator mounted to said inlet delivery duct, said swirl generator comprising a plurality of swirl vanes radially distributed within said inlet delivery duct and a flared bluffbody mounted to said plurality of swirl vanes to extend at least partially downstream of said plurality of liquid propellant injectors, at least one of said plurality of liquid propellant injectors are defined by said flared bluffbody; and a feed system to transport a liquid oxidizer and a liquid fuel, said feed system operable to convert either the liquid fuel or the liquid oxidizer to a gaseous state for communication upstream of said swirl generator, the other of said liquid oxidizer and said liquid fuel for communication to said liquid propellant injectors. 2. The rocket engine of claim 1 further comprising a first nozzle downstream of said combustor chamber. 3. The rocket engine of claim 2 further comprising an exterior thrust chamber assembly concentrically positioned around said first nozzle such that said first nozzle discharges into said exterior thrust chamber assembly. 4. The rocket engine of claim 3 wherein said exterior thrust chamber assembly further comprises: a main exterior nozzle connected to an exterior throat and concentrically positioned around said first nozzle; a secondary exterior nozzle extending from said main exterior nozzle; and a deflection nozzle disposed between said main exterior nozzle and said first nozzle. 5. The rocket engine of claim 1 wherein the feed system routes either the liquid oxidizer or the liquid fuel along the combustor chamber to transfer heat from the combustor chamber to convert the liquid oxidizer or the liquid fuel to the gaseous state. 6. The rocket engine of claim 4 and further comprising a dump step positioned between the swirl vanes and the dump step. 7. The rocket engine of claim 4 wherein the swirl vanes have a diameter of approximately 17.272 cm (6.8 inches). 8. The rocket engine of claim 6 wherein the swirl generator further comprises a centerbody having a diameter of at least approximately 3.81 cm (1.5 inches) positioned between the swirl vanes and the bluffbody. 9. The rocket engine of claim 1 wherein the feed system comprises a gas pressure feed system incorporating a regenerative heat transfer system. 10. The rocket engine of claim 1 wherein the feed system comprises a turbo-pump feed system incorporating a regenerative heat transfer system. 11. The rocket engine of claim 10 wherein the turbo-pump feed system comprises a closed loop. 12. The rocket engine of claim 10 wherein the turbo-pump feed system includes a pre-burner to gasify either the oxidizer or the fuel. 13. The rocket engine of claim 4, wherein said deflection nozzle includes an outwardly oriented annular throat and an outer wall contour to deflect combustion gases into a nearly axial direction. 14. The rocket engine of claim 1, wherein said swirl generator produces a turbulent flowfield of the fuel and oxidizer rocket propellants within said combustor chamber. 15. The rocket engine of claim 14, wherein said combustor chamber at least partially contains a combustion process of the fuel and oxidizer rocket propellants so as to produce thrust. 16. The rocket engine of claim 1, wherein at least one of said plurality of liquid propellant injectors are defined by a centerbody of said flared bluffbody. 17. A rocket engine comprising: a combustor chamber; a plurality of liquid propellant injectors in communication with said combustor chamber; a swirl generator at least partially within said combustor chamber, said swirl generator comprising a plurality of swirl vanes which support a bluffbody which extends at least partially downstream of said plurality of liquid propellant injectors, at least one of said plurality of liquid propellant injectors are defined by said bluffbody; and a feed system to transport a liquid oxidizer and a liquid fuel, said feed system operable to convert either the liquid fuel or the liquid oxidizer to a gaseous state for communication upstream of said swirl generator, the other of said liquid oxidizer and said liquid fuel for communication to said liquid propellant injectors. 18. The rocket engine of claim 17, wherein said bluffbody is defined along a centerling of said combustor chamber. 19. The rocket engine of claim 18, wherein said bluffbody is a flared bluffbody. 20. The rocket engine of claim 18, wherein said bluffbody is a solid-flared conical bluffbody. 21. The rocket engine of claim 17, wherein said bluffbody is a channeled bluffbody. 22. The rocket engine of claim 17, wherein said combustor chamber defines a combustor length to diameter ratio, L/D, of less than 1.6.