| CPC B64D 35/02 (2013.01) [B64C 11/28 (2013.01); B64D 27/12 (2013.01); B64D 27/24 (2013.01); B64D 27/026 (2024.01); B64D 2221/00 (2013.01)] | 23 Claims |
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1. A hybrid-electric powertrain for an aircraft, the hybrid-electric powertrain comprising:
a fuel source;
a gas turbine propulsion engine including a first propulsor and a gas turbine engine to drive the first propulsor to produce thrust, the gas turbine engine including a combustion chamber and an inter-turbine burner, the combustion chamber and the inter-turbine burner fluidly coupled to the fuel source;
a generator operably coupled to a drive shaft of the gas turbine engine;
a clutch between the generator and the drive shaft; and
an electric propulsion unit including a second propulsor, a plurality of blades moveable between an unfolded position and a folded position, and an electric motor to drive the second propulsor to produce thrust, wherein,
during a first mode of operation, the gas turbine propulsion engine and the electric propulsion unit are activated to produce thrust, the generator is coupled to the drive shaft via the clutch, the generator is driven by the gas turbine engine to produce electrical power to power the electric propulsion unit and each of the combustion chamber and the inter-turbine burner receive fuel from the fuel source, and the plurality of blades are in the unfolded position, and
during a second mode of operation, the gas turbine propulsion engine is activated to produce thrust, the generator is disconnected from the drive shaft via the clutch, the electric propulsion unit is deactivated, the plurality of blades are in the folded position, and the combustion chamber receives fuel from the fuel source, a fluid flow path between the inter-turbine burner and the fuel source closed during the second mode of operation.
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