Patent ID: 11898499
Assignee: THE BOEING COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 11:
12. An aircraft comprising:
an aircraft system that operates on bleed air;
a gas turbine engine having a high-pressure drive shaft and a low-pressure drive shaft; and
a power transfer system including:
an auxiliary turbine;
one or more fluid lines coupled between a bleed port on the gas turbine engine, the auxiliary turbine, and the aircraft system; and
a differential having an input shaft, a first output shaft, and a second output shaft, the auxiliary turbine coupled to the input shaft, the second output shaft in gear with the high-pressure drive shaft of the gas turbine engine, such that during a first mode of operation, power is transferred from the auxiliary turbine to the high-pressure drive shaft of the gas turbine engine.