Patent ID: 6510683
Filing Date: 2003-01-28
Classification: F02C,F02K,Y02E,Y02T

Abstract:
An apparatus for generating power, comprising:(a) a support structure, said support structure comprising (i) an oxidant supply conduit, and (ii) a first housing portion with a rotor side surface, and (iii) a second housing portion with a rotor side surface; (b) a first output shaft, said first output shaft rotatably secured with respect to said support structure; (c) a rotor having a radius R, wherein said rotor (i) is connected to said first output shaft to provide rotary motion of said first output shaft upon rotation of said rotor, (ii) comprises at least one material having a specific strength capability in excess of 683,220 inches, (iii) comprises a first surface portion, said first surface portion rotatably positioned in a close fitting, first spaced apart relationship adjacent to said rotor side surface of said first housing portion, and (iv) comprises a second surface portion, said second surface portion rotatably positioned in a close fitting, second spaced apart relationship adjacent to said rotor side surface of said second housing portion, and (v) wherein each of said first and said second spaced apart relationships are defined by a gap width â€œsâ€  which is small compared to radius â€œRâ€  of said rotor, to at least a partially house said rotor in a tight fitting relationship, so as to minimize aerodynamic drag on said rotor; (d) one or more ramjet thrust modules, said one or more ramjet thrust modules (i) each secured to said rotor for rotation therewith, (ii) each further comprise an inlet and an outlet, and wherein said inlet and said outlet are substantially aligned in a linear configuration with respect to an inlet airflow, (iii) each further comprise a shaped external portion, said shaped external portion comprising a substantially constant cross-sectional size when sequentially examined in cross-section perpendicular to the axis of an inlet airflow from a forward cross-section to a rearward cross-section, to thereby minimize pressure drag when said one or more ramjet thrust modules operate at an inlet airflow velocity M0 of at least Mach 1.5, and (iv) each of which mixes fuel supplied thereto with an oxidant supplied via said oxidant supply conduit in said support structure, to burn said fuel to generate hot combustion gas which escapes from said one or more ramjet thrust modules, producing thrust, thereby propelling said one or more ramjet thrust modules to turn said rotor and said first output shaft, thus providing shaft power output from said apparatus.