Turbine bypass turbojet with mid-turbine reingestion and method

Details Turbine bypass turbojet with mid-turbine reingestion and method Turbine bypass turbojet with mid-turbine reingestion and method

1981-09-29

1984-05-15

Croyle, Carlton R.

Power plants

Reaction motor

Method of operation

60262, 60 3917, 60 3925, F02F 302

Patent

active

044480199

ABSTRACT:
A supersonic two spool turbojet engine capable not only of developing sufficient power to accelerate up to supersonic cruise and maintain efficient operation at supersonic cruise, but also arranged 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 first stage of the turbine section so that the corrected flow to the first turbine stage remains substantially constant for high and low power setting of the engine. The bypass flow is then directed into the area between the first and second turbine to combine with the gaseous flow passing through the first turbine and pass through the second turbine.

REFERENCES:
patent: 2858671 (1958-11-01), Fox
patent: 3641766 (1972-02-01), Uehling
May, R. J. et al., "Influence of Variable Turbine Geometry on Engine Installation & Selection", USAF Paper AFAPL-TR-73-18, Nov. 1972.

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