US 11,987,377 B2
Turbo expanders 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. 17/860,746.
Prior Publication US 2024/0010351 A1, Jan. 11, 2024
Int. Cl. B64D 37/30 (2006.01); B64D 15/12 (2006.01); B64D 41/00 (2006.01); F02C 3/22 (2006.01); F02C 7/32 (2006.01)
CPC B64D 37/30 (2013.01) [B64D 15/12 (2013.01); B64D 41/00 (2013.01); F02C 3/22 (2013.01); F02C 7/32 (2013.01); F05D 2220/323 (2013.01); F05D 2220/76 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft propulsion system, comprising:
aircraft systems comprising at least one hydrogen tank and an aircraft-systems heat exchanger; and
engine systems comprising at least a main engine core, a high pressure pump, a 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;
wherein hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion,
wherein the turbo expander comprises a rotor separated into a first expander portion and a second expander portion arranged about an output shaft, and
wherein the output shaft is operably connected to a generator configured to generate electrical power, and
a secondary tank configured to contain a secondary fluid that is supplied to the turbo expander and configured to provide at least one of seal buffering and a starting flow for the turbo expander.