US 12,246,843 B2
Hybrid turbine and multiple-spool electric power system for aircraft
Evelyn M. Matheson, Bothell, WA (US); Dorina L Hester, Bothell, WA (US); Kolten Carrington Miller, Snoqualmie, WA (US); Eugene V. Solodovnik, Kenmore, WA (US); Shengyi Liu, Sammamish, WA (US); and Kamiar Karimi, Kirkland, WA (US)
Assigned to The Boeing Company, Arlington, VA (US)
Filed by The Boeing Company, Arlington, VA (US)
Filed on Feb. 7, 2023, as Appl. No. 18/165,858.
Prior Publication US 2024/0262516 A1, Aug. 8, 2024
Int. Cl. B64D 27/24 (2024.01); B64D 27/00 (2006.01); B64D 31/00 (2024.01); H02K 7/00 (2006.01); H02K 7/18 (2006.01)
CPC B64D 27/24 (2013.01) [B64D 31/00 (2013.01); H02K 7/003 (2013.01); H02K 7/1815 (2013.01); B64D 2027/005 (2013.01); B64D 2221/00 (2013.01)] 27 Claims
OG exemplary drawing
 
1. In a hybrid power system for an aircraft, the hybrid power system having an engine and a high-voltage DC (HVDC) bus interconnecting a generator-motor system, an AC distribution system, and a DC distribution system, a method for generating and using electric power, the method comprising:
operating the engine through a plurality of different operation phases, the engine having a high-pressure spool (HPS) shaft coupled with an HPS generator/motor of the generator-motor system and a low-pressure spool (LPS) shaft coupled with an LPS generator/motor of the generator-motor system;
selectively controlling at least one connection of the generator-motor system to the HVDC bus to provide, based on thrust demands of the engine, electric power from the HVDC bus to the generator-motor system to assist the engine in providing thrust;
selectively extracting, using the engine driving the generator-motor system with one or both of the HPS shaft and the LPS shaft, electric power from the engine; and
selectively delivering the electric power extracted from the engine to one or both of the AC distribution system and the DC distribution system by controlling a different connection of the generator-motor system to the HVDC bus.