Method of nacelle air heat exchanger integration for a hydrogen fueled fuel cell powered aircraft

A heat exchanger system for an aircraft comprising:

• a nacelle having an inlet and an outlet, wherein air flowing into the nacelle through the inlet and out of the nacelle through the outlet;
• a nacelle heat exchanger within the nacelle, wherein the nacelle heat exchanger is configured to transfer heat away from the air in an airflow to the nacelle heat exchanger, wherein the nacelle heat exchanger is oriented substantially parallel to a direction of flight of the aircraft, wherein the nacelle heat exchanger comprises a hollow geometric conduit with a channel, wherein the airflow passes through an exterior surface of the hollow geometric conduit from exterior of the channel to interior of the channel;
• and
• a fuel cell stack located within the channel of the hollow geometric conduit.

An aircraft comprising:

• a fuselage;
• a first wing and a second wing connected to the fuselage;
• engines connected to the first wing and the second wing, wherein each engine in the engines comprises:
• a nacelle;
• an electric motor within the nacelle;
• a fuel cell stack within the nacelle;
• and
• a nacelle heat exchanger within the nacelle, wherein the nacelle heat exchanger is configured to transfer heat away from a coolant using air in an airflow to the nacelle heat exchanger, wherein the nacelle heat exchanger comprises a hollow geometric conduit with a channel, wherein the airflow passes through an exterior surface of the hollow geometric conduit from exterior of the channel to interior of the channel;
• and
• a fan system within the nacelle, wherein the fan system is configured to increase the airflow to the nacelle heat exchanger;
• wherein the electric motor and the fuel cell stack are located within the channel of the hollow geometric conduit.