Convertible turbo-fan, turbo-shaft aircraft propulsion system

Patent · Tue Mar 24 00:00:00 EST 1987

OSTI ID:6618933

Ossi, R R

A composite gas turbine engine propulsion system for aircraft which includes a propulsion fan for providing forward thrust as a first mode of operation and a turbo-shaft power output for driving an external load as a second mode of operation and means for selectably changing between the modes of operation and combinations thereof comprising: a gas turbine engine mounted to a frame providing power to a drift shaft; first transmission means connected to the drive shaft for providing a power output suitable for driving the external load; second transmission means connected to the drive shaft for providing a variable power output suitable for driving the propulsion fan, the second transmission comprising; a gear reduction system operatively connected to the drive shaft and constructed to provide output power to an output shaft suitable for driving the fan, the gear reduction system comprising a sun gear operatively connected for rotation with the drive shaft; a planet gear carrier fixed to the engine frame; planet gears mounted in the planet gear carrier in operative engagement with the sun gear; a bell gear mounted for rotation in operative engagement with the planet gears and having a shaft extending therefrom to provide the output of the gear reduction system; and a torque converter.

• Assignee: Avco Corp., Stratford, CT
• Patent Number(s): US 4651521
• OSTI ID: 6618933
• Resource Relation: Patent File Date: Filed date 21 Nov 1985
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
AIRCRAFT
GAS TURBINE ENGINES
TURBOFAN ENGINES
BLOWERS
SHAFTS
DESIGN
OPERATION
GEARS
MECHANICAL TRANSMISSIONS
PROPULSION SYSTEMS
ROTATION
SPEED REGULATORS
STATORS
TORQUE
VELOCITY
CONTROL EQUIPMENT
ENGINES
EQUIPMENT
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINE PARTS
MOTION
330103* - Internal Combustion Engines- Turbine