US 12,291,995 B2
Hybrid electric single engine descent power extraction control
Martin Richard Amari, Glastonbury, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Oct. 24, 2022, as Appl. No. 17/971,955.
Claims priority of provisional application 63/273,542, filed on Oct. 29, 2021.
Prior Publication US 2023/0136062 A1, May 4, 2023
Int. Cl. F02C 6/00 (2006.01); B64D 27/10 (2006.01); B64D 27/24 (2006.01); B64D 31/12 (2006.01); F02C 7/00 (2006.01); F02C 9/42 (2006.01); G05D 1/00 (2006.01); B64D 27/02 (2006.01)
CPC F02C 6/00 (2013.01) [B64D 27/10 (2013.01); B64D 27/24 (2013.01); B64D 31/12 (2013.01); F02C 7/00 (2013.01); F02C 9/42 (2013.01); G05D 1/101 (2013.01); B64D 27/026 (2024.01)] 20 Claims
OG exemplary drawing
 
1. A system of a hybrid aircraft, the system comprising:
a first gas turbine engine comprising a first fan, a first low spool electric machine, and a first high spool electric machine;
a second gas turbine engine comprising a second fan, a second low spool electric machine, and a second high spool electric machine; and
a controller operable to:
determine an operating mode of the hybrid aircraft;
control power extraction from the first low spool electric machine and the first high spool electric machine while a single engine descent mode is active, wherein power extraction from the first high spool electric machine is initially used as a primary source of electric power while the first gas turbine engine is driven above idle during descent of the hybrid aircraft, and power is extracted from the first low spool electric machine based on determining that a speed of the first fan results in excess thrust; and
provide electric power to either or both of the second low spool electric machine and the second high spool electric machine while the single engine descent mode is active to balance thrust between the first gas turbine engine and the second gas turbine engine, wherein electric power provided to the second low spool electric machine drives rotation of the second fan to balance thrust between the first gas turbine engine and the second gas turbine engine.