Dual cycle aircraft turbine engine

Details Dual cycle aircraft turbine engine Dual cycle aircraft turbine engine

1973-09-06

1977-07-05

Croyle, Carlton R.

Power plants

Reaction motor

Interrelated reaction motors

60263, 415145, F02K 306

Patent

active

040331199

ABSTRACT:
A method and apparatus applicable to jet engines for improving operating efficiency over broad ranges of flight conditions and for reducing engine noise output in take-off and landing by controlling the airflow entering and exiting the engines. A turbojet engine apparatus is described which operates efficiently at both subsonic and supersonic speeds and a method is described which enables a turbofan with an associated satellite turbojet or turbofan to operate more efficiently at both subsonic and supersonic speeds. In both cases, take-off and landing noise is reduced substantially. The apparatus consists essentially of arranging for two separate portions of an engine to act upon one airstream or, alternately, to operate on independent airstreams.

REFERENCES:
patent: 2823516 (1958-02-01), Schelp
patent: 3149461 (1964-09-01), Eichholtz
patent: 3769797 (1973-11-01), Stevens

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