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Using Air Bypass to Cool Rocket Engine.png

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The title ( referring to "rocket" engine) is somewhat misleading to me.  The diagram shows a turbine engine with a by-pass fan.  This arrangement is typically used in commercial aircraft.  

An air-breathing engine, such as shown in the diagram, is not in the same class as a rocket engine which (usually) burns fuel or propellant by introducing oxygen (or another oxidizer).  The fuel and oxidizer constituents are either premixed or mixed at the point of combustion.  If liquid hydrogen and/or oxygen are used, the cold liquid can be used to cool various engine parts before it is vaporized for combustion.

In the diagram above, some of the discharge from the bypass fan goes into the compressor stage.  In this instance, there appear to be 4 axial compression stages and a final mixed-flow or centrifugal stage.  At the hot end, the hot gas expands through 4 axial turbine stages.  One or more of the turbine stages drives the fan while the remaining turbine stages drive the compressor section.  The diagram does not provide sufficient detail to show the shaft and bearing arrangement.

The remaining output from the fan is discharged at the rear of the engine to generate thrust, along with the hot gas exiting the final turbine stage.     

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