US 12,071,257 B2
Hybrid electric hydrogen engine for aircraft
Neil J. Terwilliger, Cheshire, CT (US); and Joseph B. Staubach, Colchester, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Jul. 8, 2022, as Appl. No. 17/860,733.
Prior Publication US 2024/0010350 A1, Jan. 11, 2024
Int. Cl. B64D 37/30 (2006.01); B64D 37/34 (2006.01); B64D 41/00 (2006.01); F02D 41/00 (2006.01)
CPC B64D 37/30 (2013.01) [B64D 37/34 (2013.01); F02D 41/0027 (2013.01); B64D 2041/005 (2013.01)] 14 Claims
OG exemplary drawing
 
1. An aircraft engine system, comprising:
a core assembly comprising a compressor section, a combustor section, and a turbine section arranged along a shaft, with a core flow path through the core assembly such that exhaust from the combustor section passes through the turbine section and exits through a nozzle;
a fuel cell configured to generate electrical power;
a cryogenic fuel source configured to supply a fuel through a fuel supply line to each of the combustor section for combustion and the fuel cell for reaction to generate the electrical power;
a battery electrically connected to the fuel cell and configured to store electrical power; and
a system controller configured to selectively direct the fuel from the cryogenic fuel source to each of the combustor section and the fuel cell, wherein the system controller is configured to:
determine a state of electrical power demand associated with at least one of the aircraft engine system or an aircraft associated with the aircraft engine system relative to a threshold power requirement;
determine a current power capacity of the battery;
determine if an amount of fuel in the fuel supply line is in excess of that necessary for operation of the core assembly; based on a determination that excess fuel is present, the system controller is configured to direct at least a portion of the excess fuel from the fuel supply line to the fuel cell to generate the electrical power;
based on a determination that the state of the electrical power demand is above the threshold power requirement, direct at least a portion of the generated electrical power to the respective aircraft engine system or aircraft;
based on a determination that a current power capacity of the battery is below a threshold power capacity, direct at least a portion of the generated electrical power to the battery to charge the battery; and
based on a determination that the state of the electrical power demand is at or below the threshold power requirement and a determination that the current power capacity of the battery is at or above the threshold power capacity, vent the excess fuel from the fuel supply line.