Patent ID: 11867126
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 8:
9. A gas turbine engine system comprising :
a first turboprop engine and a second turboprop engine supported by wings on opposite sides of a fuselage, each of said first and second turboprop engines having
an engine core;
a core output shaft drivable by the engine core;
a power output shaft;
an auxiliary power shaft;
a reduction gearbox having gears drivingly connecting the core output shaft to the auxiliary power shaft, the gears including an epicyclic gearing, the epicyclic gearing drivingly connecting the core output shaft and the auxiliary power shaft to the power output shaft;

the gas turbine engine system further comprising a mechanical connexion drivingly connecting the auxiliary power shaft of the first and second turboprop engines to one another; and
wherein the epicyclic gearing of one of the first and second turboprop engine reverses an angular rotation direction between the auxiliary power shaft and the power output shaft.