The application discloses an integrated
aviation hybrid power
oil cooling system and an
aviation hybrid power aircraft, and belongs to the technical field of
aviation hybrid power aircrafts. The integrated aviation
hybrid power oil cooling system comprises a fan, a fan flow channel piece with an annular flow channel, an annular radiator, an
oil supply and return pump set, a fan motor, a fan
motor controller and an
oil tank. The axial ends of the fan flow channel piece are connected with the fan and the annular radiator respectively, so that the annular flow channel is axially communicated with the fan and the annular radiator, and then the cooling
airflow generated by the fan enters the annular radiator through the annular flow channel. The inner shaft hole of the fan flow channel piece further forms a hub installation space for installation. The fan motor and the
oil supply and return pump set are arranged in the hub installation space respectively, two
power output ends of the fan motor are connected with the fan and the
oil supply and return pump set respectively, the
oil tank is arranged in the shaft hole of the annular radiator, and the fan
motor controller is connected with the fan flow channel piece. The overall structure of the application is compact and reasonable, the manufacturing and maintenance costs are low, the weight is small, and the
utilization rate of the cooling
airflow heat dissipation capacity is high.