US 12,359,623 B1
Hydrogen turboexpander for use in an aviation propulsion system
Russell Stratton, Toronto (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Apr. 9, 2024, as Appl. No. 18/630,587.
Int. Cl. F02C 7/22 (2006.01); B64D 27/10 (2006.01)
CPC F02C 7/22 (2013.01) [B64D 27/10 (2013.01); F05D 2260/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft propulsion system, comprising:
a gas turbine engine having a compressor section, a combustion section having a combustor, a turbine section, and a turbine exhaust section, wherein the gas turbine engine is in drive communication with a rotational load component;
a hydrogen-exhaust heat exchanger disposed relative to the turbine exhaust section so that a flow of exhaust gas exiting the turbine section is in communication with the hydrogen-exhaust heat exchanger, wherein the hydrogen-exhaust heat exchanger is configured to change a flow of liquid hydrogen from a source of liquid hydrogen to a flow of gaseous hydrogen; and
a hydrogen turboexpander having a first rotor shaft and a second rotor shaft disposed parallel one another within a housing, the housing including a first rotor shaft cavity configured to receive the first rotor shaft and a second rotor shaft cavity configured to receive the second rotor shaft, the housing further including an inlet port to receive the flow of gaseous hydrogen and an exit port for the flow of gaseous hydrogen to exit the hydrogen turboexpander, wherein the first rotor shaft and the first rotor shaft cavity define a first rotor shaft fluid flow path (RSFFP), and the second rotor shaft and the second rotor shaft cavity define a second RSFFP;
wherein the hydrogen turboexpander is configured with the first RSFFP in series with the second RSFFP between the inlet port and the exit port; and
wherein the exit port is in fluid communication with the combustor.