A compound engine assembly (10) for use as an auxiliary power unit for an aircraft and including an engine core (12) with internal combustion engine(s), a compressor (18) having an outlet (18o) in fluid communication with an engine core inlet (12i), a bleed conduit (74) in fluid communication with the compressor outlet (12o) through a bleed air valve, and a turbine section (20) having an inlet (20i) in fluid communication with the engine core outlet (20o) and configured to compound power with the engine core (12). The turbine section (20) may include a first stage turbine (22) having an inlet (22o) in fluid communication with the engine core outlet (12o) and a second stage turbine (24) having an inlet (24i) in fluid communication the first stage turbine outlet (22o). A method of providing compressed air and electrical power to an aircraft is also discussed.
COMPOUND ENGINE ASSEMBLY WITH BLEED AIR
VERBUNDTRIEBWERKANORDNUNG MIT ZAPFLUFT
ENSEMBLE MOTEUR COMBINÉ AVEC DE L'AIR DE PRÉLÈVEMENT
2018-09-26
Patent
Elektronische Ressource
Englisch