Compact, high performance swirl combustion rocket engine

A compact rocket engine with advanced swirl combustion can generate vacuum thrust in the 500 1b f to 100,000 1b f range. The rocket engine (10) includes a feed system (21), combustor assembly (12), swirl generator (14) and nozzle (16). The feed system (21) delivers the oxidizer and fuel (18,20) to the combustor assembly (12) in the proper phase suitable for use with the swirl generator (14), which is positioned within the combustor assembly (12). This causes a highly turbulent three-dimensional swirling flowfield produced for rapid and efficient mixing and burning of the fuel/oxidizer combustion products, which are expanded through the nozzle (16) to produce thrust. The aerothermochemical processes are extremely efficient, and consequently produce nearly ideal thrust levels. Swirl enhanced combustion significantly reduces combustor length, weight, complexity and cost, yet provides high propulsion efficiencies and wide rocket engine (10) throttling operability. In one embodiment, the rocket engine is integrated into a dual-throat, expansion/deflection rocket engine to provide deep throttleability with high Isp.