| 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 disc rotor (114) is disclosed. An unshrouded ramjet inlet (120) compresses an impinging inlet air stream by utilizing the thrust module inlet structures and an adjacent housing sidewall (105, 106). Fuel is oxidized in the ramjet thrust 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 in the inlet shock and short residence times in the combustion chamber enabling low nitrogen oxides emissions to be achieved. |
