Self-adaptive aviation high-temperature hydrogen fuel cell air-cooling heat dissipation system and design method thereof

Abstract

The invention relates to a self-adaptive aviation high-temperature hydrogen fuel cell air cooling heat dissipation system and a design method thereof, and the heat dissipation system comprises a high-temperature hydrogen fuel cell, a cooling fan, an exhaust gas turbine, a rotating speed sensor, an electromagnetic valve and a controller, and is provided with a cooling gas channel and a reaction exhaust gas channel. Cooling gas is introduced from the atmosphere, flows through the fuel cell cooling channel and the cooling fan and then is discharged; after reaction waste gas is discharged from the fuel cell, part of the reaction waste gas passes through the waste gas turbine and part of the reaction waste gas is discharged into atmosphere. The waste gas turbine, the cooling fan and the rotating speed sensor are coaxial to form an integrated driving unit, the waste gas drives the turbine to drive the fan to operate, the rotating speed sensor transmits a rotating speed signal to the controller, and self-adaptive air cooling heat dissipation is achieved. According to the invention, the air-cooling heat dissipation system is located in an aircraft belly equipment compartment, uniform cooling air with enough pressure can be provided for heat exchange of the fuel cell in the whole flight envelope, and no external energy is needed.

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