CPC B64D 27/24 (2013.01) [B64C 21/06 (2013.01); B64D 27/18 (2013.01); B64D 27/20 (2013.01); B64D 2027/026 (2013.01); B64D 2205/00 (2013.01); Y02T 50/10 (2013.01); Y02T 50/60 (2013.01); Y10S 903/905 (2013.01); Y10S 903/906 (2013.01); Y10S 903/907 (2013.01)] | 20 Claims |
1. A gas-electric propulsion system for an aircraft comprising a fuselage and a wing, the system comprising:
a gas turbine engine coupled to the wing of the aircraft or coupled to the fuselage of the aircraft;
an electric powered boundary layer ingestion fan positioned aft of the wing;
an electric generator driven by the gas turbine engine and electrically coupled to the boundary layer ingestion fan, wherein the electric generator converts rotational energy from the gas turbine engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan; and
a battery electrically coupled to the electric generator and to the boundary layer ingestion fan.
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