An aircraft pneumatic system comprises a gas turbine engine (10) comprising a compressor (14), a fan (12) and a core turbine (12) coupled to one of the compressor (14) and the fan (12), an auxiliary turbine (50) having an inlet in fluid communication with the core turbine (20), the auxiliary turbine (50) being configured to power an auxiliary compressor (40), an inlet of the auxiliary compressor (40) being in fluid communication with an outlet of the fan (12), and an outlet of the auxiliary compressor (40) being in fluid communication with an aircraft environmental control system (48).
Aircraft pneumatic system
2018-07-04
Patent
Electronic Resource
English