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

Claim 13:
14. A method of operating a gas turbine engine system having 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 and a reduction gearbox interconnecting the core output shaft, power output shaft and auxiliary power shaft, the reduction gearbox having an epicyclic gearing reduction stage, the method comprising :
the auxiliary power shaft of the first turboprop engine driving the power output shaft of the first turboprop engine;
the core output shaft of the second turboprop engine driving the power output shaft of the second turboprop engine;
the epicyclic gearing reduction stage of the first turboprop engine reversing an angular rotation direction between the corresponding auxiliary power shaft and power output shaft; and
the epicyclic gearing reduction stage of the second turboprop engine preserving an angular rotation direction between the corresponding auxiliary power shaft and power output shaft.