Aerospace fuel cell system integration
AssigneeHyflyer Powertrain, LLC
InventorsJesse Michael Schneider, Liviu Ion Cosacescu, John R. Fulton
Life of this patent
Estimating the term…
Abstract
A fuel cell system configured to provide electrical power to an electrical motor producing propulsive thrust for an aircraft includes a plurality of fuel cell stacks radially arranged about a central cavity. Fuel cell plates within each of the fuel cell stacks are oriented such that major surfaces of the fuel cell plates are parallel to an airflow created by the aircraft as it moves through the air. The fuel cell system further includes a plurality of cooling devices disposed in radial cavities located between at least two fuel cell stacks in the plurality of fuel cell stacks.
Claims21
A fuel cell system configured to provide electrical power to an electrical motor producing propulsive thrust for an aircraft, comprising:
- a plurality of fuel cell stacks radially arranged about a central cavity and wherein fuel cell plates within each of the fuel cell stacks are oriented such that major surfaces of the fuel cell plates are parallel to an airflow created by the aircraft as it moves through the air;
- and
- a plurality of cooling devices disposed in radial cavities located between at least two fuel cell stacks in the plurality of fuel cell stacks.
An aircraft, comprising:
- A fuel cell system mounted within a nacelle on the aircraft;
- an electrical motor powered by the fuel cell system having a drive shaft;
- an air movement device connected to the drive shaft and configured to provide reactant air to fuel cell plates in the fuel cell system;
- and
- a propeller located external to the nacelle and connected to the drive shaft, wherein the propeller is configured to provide propulsive thrust for the aircraft.
An aircraft, comprising:
- a fuel cell system mounted within the aircraft;
- an electrical motor powered by the fuel cell system having a drive shaft;
- a thrust producing device connected to the drive shaft and configured to pressure air within a nacelle and to provide reactant air to the fuel cell system;
- and
- a bypass chamber in a nacelle configured to route a portion of air accelerated by the thrust producing device such that it bypasses the fuel cell system, wherein this air accelerated by the thrust producing device provides propulsive thrust for the aircraft as it exits the nacelle.
21-52. (canceled)
Dependencies are inferred from the claim text.