US 11,867,126 B2
Gas turbine engine and method of operation
Bruno Chatelois, Boucherville (CA); Michel Desjardins, St-Hubert (CA); Paul Weaver, Chateauguay (CA); and Eric Durocher, Boucherville (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jul. 13, 2021, as Appl. No. 17/373,849.
Prior Publication US 2023/0016164 A1, Jan. 19, 2023
Int. Cl. F02C 7/32 (2006.01); F02C 6/20 (2006.01); F02C 7/36 (2006.01)
CPC F02C 7/32 (2013.01) [F02C 6/206 (2013.01); F02C 7/36 (2013.01); F05D 2220/323 (2013.01); F05D 2220/74 (2013.01); F05D 2220/76 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
an engine core;
a core output shaft drivable by the engine core;
a power output shaft;
an auxiliary power shaft; and
a reduction gearbox having an input port operatively connected to the core output shaft, an output port operatively connected to the power output shaft, an auxiliary port operatively connected to the auxiliary power shaft, and epicyclic gearing drivingly connecting the core output shaft to the auxiliary power shaft, the epicyclic gearing drivingly connecting the core output shaft and the auxiliary power shaft to the power output shaft;
wherein the auxiliary power shaft is drivingly connected to another gas turbine engine.