| 摘要 |
A supersonic jet engine capable not only of developing sufficient power to accelerate up to supersonic cruise and maintain efficient operation at supersonic cruise, but also arrange to cruise at subsonic velocities with a relatively low specific fuel consumption. The engine is provided with a variable bypass passageway downstream of the compressor. Flow into the bypass passageway is controlled so that during low power setting the bypass passageway is closed so that all the gaseous flow is directed through the turbine. During higher power settings, the bypass passageway is opened to the extent that a selected portion of the gaseous flow is directed through the bypass passageway to bypass the turbine, so that the corrected flow to the turbine remains substantially constant for both high and low power settings of the engine. The turbine has first and second stages, with the first stage receiving all of the gaseous flow that is not directed through the bypass passageway. The gaseous flow from the turbine first stage is split into first and second portions, with the first portion being directed through a coannular inner passageway to drive the turbine second stage, and the second portion of the gaseous discharge being directed toward a coannular outer passageway to be discharged in a coannular pattern radially outwardly of the first portion of gaseous flow.
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