| 摘要 |
A turbojet propulsion engine for supersonic aircraft has a primary unit including a compressor, a combustion chamber, a turbine which drives the compressor, and an exhaust assembly, and a secondary unit including a compression fan assembly arranged in an annular secondary duct surrounding the primary unit, the fan assembly having at least one stage of rotor blades rigidly connected to the shaft which drives the compressor of the primary unit and is disposed between an upstream stage of fixed inlet guide vanes and a downstream stage of fixed flow straightener vanes, the inlet guide vane stage and the flow straightener vane stage each being associated with an adjuster for adjusting the pitch of the respective vanes.
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