An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.
Auxiliary power unit with variable speed ratio
2019-03-26
Patent
Electronic Resource
English
IPC: | F02B INTERNAL-COMBUSTION PISTON ENGINES , Brennkraftmaschinen mit innerer Verbrennung mit Verdrängerwirkung / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02G HOT-GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS , mit Heißgas oder Verbrennungsgasen betriebene Kraftmaschinenanlagen, wobei die Kraftmaschinen mit Verdrängerwirkung arbeiten |