A propulsion system (18) for an aircraft, comprising: a gas turbine engine having at least a high pressure (HP) spool (24) and a low pressure (LP) spool (26), wherein the LP spool (26) is operative to drive a propulsor (28); and a hybrid auxiliary power unit (APU) (22) mechanically coupled to both the HP spool (24) and the LP spool (26), wherein the hybrid APU (22) includes an APU compressor (60); an APU turbine (64); and a fuel cell (62) fluidly disposed between the APU compressor (60) and the APU turbine (64), wherein the fuell cell (62) is operative to receive as an oxidant air pressurized by the APU compressor (60); to generate electrical power using a fuel and the oxidant; to heat the air pressurized by the APU compressor (60); and to discharge the heated pressurized air into the APU turbine (64), wherein the hybrid APU (22) is operative to supply rotational power to both the HP spool (24) and the LP spool (26).
Propulsion system for an aircraft, aircraft and method of operating a propulsion system
Antriebssystem für ein Flugzeug sowie Verfahren zum Betreib eines Antriebssystems
Système de propulsion pour avion et procédé d'opération d'un tel système
2018-10-31
Patent
Electronic Resource
English