| 摘要 |
A turbocompressor assembly includes a first rotor stage mounted on a rotary shaft and including circular rows of impeller blades on one surface thereof separated by radial gaps in which opposed blade rows on a second rotor stage are received. The two rotor stages are geared for counter-rotation and at least one of the rotors is perforated proximate its center to allow air to be drawn between the opposed surfaces thereof, where its passage over the impeller blades develops useful torque. The opposed rotor surfaces are convolved to define a radially decreasing separation to an annular combustion cavity, and thereafter increasing with radius. Thus a radial compressor and a turbine function are developed by the respective blade rows on either side of the combustion cavity. The combustion cavity may be formed in one of the rotors, or may be shared between the rotors as a communicating common annular chamber. Fuel may be delivered to the combustion chamber directly admixed into the air stream, or by a fuel delivery system.
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