US 12,404,803 B2
Hybrid gas turbine engine
Hervé Turcotte, Sainte-Julie (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jun. 15, 2020, as Appl. No. 16/901,383.
Prior Publication US 2021/0388732 A1, Dec. 16, 2021
Int. Cl. F01D 15/10 (2006.01); B64D 27/33 (2024.01); B64D 31/18 (2024.01); B64D 35/022 (2025.01); F01D 15/12 (2006.01); F02C 3/073 (2006.01); F02C 3/14 (2006.01); F02C 6/20 (2006.01); F02C 7/32 (2006.01); F02C 7/36 (2006.01)
CPC F02C 3/145 (2013.01) [B64D 27/33 (2024.01); B64D 31/18 (2024.01); B64D 35/022 (2024.01); F01D 15/10 (2013.01); F01D 15/12 (2013.01); F02C 3/073 (2013.01); F02C 6/206 (2013.01); F02C 7/32 (2013.01); F02C 7/36 (2013.01)] 7 Claims
OG exemplary drawing
 
1. A hybrid multi-spool aircraft gas turbine engine, comprising:
a low-pressure (LP) spool and a high-pressure (HP) spool rotatable independently of one another about a central axis, the LP spool having an LP compressor and an LP turbine drivingly engaged to the LP compressor via an LP shaft, the LP shaft drivingly engaged to a rotatable load at a first end thereof, the HP spool having an HP turbine and an HP compressor drivingly engaged to the HP turbine via a HP shaft;
an accessory gearbox (AGB) drivingly engaged to both of the LP shaft and the HP shaft and located proximate a second end of the LP shaft, the AGB having at least one accessory output drivingly engageable to at least one accessory and two inputs, the at least one accessory including a starter/generator, the AGB including a shaft drivingly engaged to the LP shaft via gears of the AGB, the shaft being radially offset from the LP shaft relative to the central axis and extending transversally to the LP shaft; and
at least two electric motors all distinct from the starter/generator and drivingly engaged to the two inputs of the AGB, the at least two electric motors drivingly engaged to the rotatable load via the AGB and the LP shaft, the at least two electric motors simultaneously drivingly engaged to opposed ends of the shaft, the HP shaft drivingly disengaged from the at least two electric motors,
wherein the hybrid multi-spool gas turbine engine is operable in a configuration in which a first power generated by the at least two electric motors and a second power generated by the LP turbine are compounded to drive the rotatable load.