	US 12,103,699 B2
	Hybrid electric power for turbine engines having hydrogen fuel systems
Brian M. Holley, Eastford, CT (US); Joseph B. Staubach, Colchester, CT (US); Marc J. Muldoon, Marlborough, CT (US); and Charles E. Lents, Amston, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Jul. 8, 2022, as Appl. No. 17/860,751.
Prior Publication US 2024/0010352 A1, Jan. 11, 2024
Int. Cl. B64D 37/30 (2006.01); B64D 37/34 (2006.01); B64D 41/00 (2006.01); F02C 3/22 (2006.01); F02C 7/224 (2006.01); F02C 7/32 (2006.01)

CPC B64D 37/30 (2013.01) [B64D 37/34 (2013.01); B64D 41/00 (2013.01); F02C 3/22 (2013.01); F02C 7/224 (2013.01); F02C 7/32 (2013.01); F05D 2220/323 (2013.01); F05D 2220/76 (2013.01); F05D 2260/40311 (2013.01)]

20 Claims

1. An aircraft propulsion system, comprising:

aircraft systems comprising at least one hydrogen tank and an aircraft-systems heat exchanger, wherein the aircraft-systems heat exchanger receives hydrogen as a first working fluid and air for supply to a cabin air cooling system as a second working fluid; and

engine systems comprising at least a main engine core, a high pressure pump, a first hydrogen-air heat exchanger, a hydrogen-oil heat exchanger, a second hydrogen-air heat exchanger, and a turbo expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section arranged along an engine shaft;

wherein hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through, in serial flow order, the aircraft-systems heat exchanger, the high pressure pump, the first hydrogen-air heat exchanger, the hydrogen-oil heat exchanger, the second hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion,

wherein the turbo expander is configured to impart power to the engine shaft by rotationally driving a generator that is electrically coupled to a motor, wherein the motor is operably coupled to the engine shaft via a transmission; and

a controller configured to control operation of the turbo expander, the generator, and the motor to at least one of control a power output from the generator and a power input from the motor to the engine shaft in response to flight conditions.

11. An aircraft comprising:

engine systems comprising at least a main engine core having a compressor section, a combustor section having a burner, and a turbine section arranged along an engine shaft, and the engine systems further comprise a high pressure pump, a first hydrogen-air heat exchanger, a hydrogen-oil heat exchanger, a second hydrogen-air heat exchanger, and a turbo expander;

aircraft systems comprising at least one hydrogen tank and an aircraft-systems heat exchanger arranged remote from the main engine core, wherein the aircraft-systems heat exchanger receives hydrogen as a first working fluid and air for supply to a cabin air cooling system as a second working fluid;