An aircraft includes a fuel cell system including a fuel cell powered by hydrogen received from a supply of hydrogen, and a propulsion unit including a conduit through which a flow of air is propelled. A first heat exchanger transfers heat from the fuel cell to a coolant fluid located in a coolant loop, and a second heat exchanger is located in the conduit for heating the air passing through the conduit by transferring heat to the air from the coolant fluid via the second heat exchanger. This configuration serves to cool the fuel cell while increasing the efficiency of the propulsion unit.

An aircraft includes a fuel cell system including a fuel cell powered by hydrogen received from a supply of hydrogen, and a propulsion unit including a conduit through which a flow of air is propelled. A first heat exchanger transfers heat from the fuel cell to a coolant fluid located in a coolant loop, and a second heat exchanger is located in the conduit for heating the air passing through the conduit by transferring heat to the air from the coolant fluid via the second heat exchanger. This configuration serves to cool the fuel cell while increasing the efficiency of the propulsion unit.

Certain aspects relate to a blended wing body aircraft with a fuel cell and methods of use. An exemplary aircraft includes a blended wing body, at least a propulsor mechanically affixed to the aircraft and configured to propel the aircraft, at least a first fuel store configured to store a first fuel, and at least a fuel cell configured to combine the first fuel with oxygen to produce electricity.

Certain aspects relate to a blended wing body aircraft with a fuel cell and methods of use. An exemplary aircraft includes a blended wing body, at least a propulsor mechanically affixed to the aircraft and configured to propel the aircraft, at least a first fuel store configured to store a first fuel, and at least a fuel cell configured to combine the first fuel with oxygen to produce electricity.

A description is given of a fuel cell comprising an electrode-membrane unit comprising a cathode and an anode, a cathodal gas diffusion element, an anodal gas diffusion element, the electrode-membrane unit being accommodated between the gas diffusion elements; a cathodal bipolar plate, and an anodal bipolar plate. Provision is made here for the cathodal gas diffusion element or/and the anodal gas diffusion element to have at least one structural element facing the respective bipolar plate and integrally bonded to the relevant gas diffusion element.

A manifold plate for a fuel cell including a plurality of openings for leading reactants towards and/or away from the fuel cell and at least one magnet providing a magnetic field which is oriented in a direction of the stack of the fuel cell. The manifold plate defines a main direction which may be seen as in a direction of a stack including electrodes forming the fuel cell. The openings of the manifold plate may be arranged along the main direction of the manifold plate and the magnet of the manifold plate may be arranged between two of the openings and may be oriented so that the direction between north pole and south pole of the magnet corresponds to the main direction.

A manifold plate for a fuel cell including a plurality of openings for leading reactants towards and/or away from the fuel cell and at least one magnet providing a magnetic field which is oriented in a direction of the stack of the fuel cell. The manifold plate defines a main direction which may be seen as in a direction of a stack including electrodes forming the fuel cell. The openings of the manifold plate may be arranged along the main direction of the manifold plate and the magnet of the manifold plate may be arranged between two of the openings and may be oriented so that the direction between north pole and south pole of the magnet corresponds to the main direction.

A system for an aircraft including: a fuel tank defining an interior; and a fuel cell assembly having a fuel cell defining an air outlet, wherein the air outlet of the fuel cell is in airflow communication with the interior of the fuel tank for providing an inerting airflow from the fuel cell to the interior of the fuel tank to reduce an oxygen content of the interior of the fuel tank.

A system for an aircraft including: a fuel tank defining an interior; and a fuel cell assembly having a fuel cell defining an air outlet, wherein the air outlet of the fuel cell is in airflow communication with the interior of the fuel tank for providing an inerting airflow from the fuel cell to the interior of the fuel tank to reduce an oxygen content of the interior of the fuel tank.

Example systems, methods, and apparatus are disclosed herein. Disclosed systems include a superconducting (SC) motor to power a propulsor of an aircraft and a liquid hydrogen (LH2) subcooling system including a primary flowline fluidly coupled to a cooling assembly of the SC motor, a secondary flowline fluidly coupled to the primary flowline, an expansion valve coupled to the secondary flowline, and a heat exchanger fluidly coupled to the primary flowline and the secondary flowline. Disclosed systems also include a fuel cell stack coupled to the primary flowline and the cooling assembly.