Ramjet engine for power generation

Abstract

A ramjet engine power generator. Supersonic ramjets are provided at the distal ends of a low aerodynamic drag rotor. The rotor is affixed at a central hub to a shaft, and rotates about an axis defined by the shaft. The rotor acts as a structural member which transmits to the shaft the thrust generated by the ramjets. In the preferred embodiment, a partially shrouded ramjet inlet captures and compresses an impinging inlet air stream by utilizing inlet structures and an adjacent housing sidewall. The compressed air inlet stream provides oxygen for mixing with a fuel, such as natural gas, other suitable hydrocarbons, or hydrogen, which is supplied to the novel, preferably replaceable ramjet combustion chamber(s). Fuel is oxidized in the combustion chamber(s) to produce expanding combustion gases. Such gases escape out through a partially shrouded nozzle, acting against three outlet structures and an adjacent housing sidewall, rotating the ramjet at supersonic velocities, and producing shaft energy. Enthalpy in escaping combustion gases is substantially segregated in an outlet duct and may be utilized thermally or mechanically via suitable heat exchange device. Efficient mixing of the oxidant and fuel prior to entry into the ramjet combustor, and the short residence times in the combustion chamber, minimize the formation of undesirable oxides of nitrogen.