| 摘要 |
A method and apparatus using partially unshrouded type supersonic ramjet thrust module(s) (118) at the periphery of a low aerodynamic drag tapered di sc rotor (114) is disclosed. An unshrouded ramjet inlet (120) compresses an impinging inlet air stream by utilizing the thrust module inlet structures a nd an adjacent housing sidewall (105, 106). Fuel is oxidized in the ramjet thru st module(s) producing combustion gases which rotate the ramjet at supersonic velocities about a shaft (108) for power generation. The enthalpy in the escaping combustion gases is substantially segregated in an outlet duct (430 ) and may be utilized thermally via a heat exchanger (440). Efficient mixing i n the inlet shock and short residence times in the combustion chamber enabling low nitrogen oxides emissions to be achieved. |
