An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods direct oil from a lubrication and cooling path to targeted sections of ice-prone surfaces to manage ice accretion in a way that does not unduly increase the total volume of oil, require larger pumps, or complicate the system.

A rotary electric machine is driven by a supply of electric power. The rotary electric machine includes a stator and a rotor. The rotor rotates about a rotation axis, and faces the stator through an axial gap in an axial direction in which the rotation axis extends. The rotor includes vanes provided inward of the axial gap in a radial direction of the rotation axis, and the vanes send gas toward the axial gap according to rotation of the rotor.

A rotary electric machine is driven by a supply of electric power. The rotary electric machine includes a stator and a rotor. The rotor rotates about a rotation axis, and faces the stator through an axial gap in an axial direction in which the rotation axis extends. The rotor includes vanes provided inward of the axial gap in a radial direction of the rotation axis, and the vanes send gas toward the axial gap according to rotation of the rotor.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

An aerodynamic stator for an air-moving device is provided. The aerodynamic stator may receive a motor or a control unit of the air-moving device in a central cavity. The aerodynamic stator may include conductive stator vanes. The conductive stator vanes may be in conductive communication with the motor or control unit. An airflow generated by the aerodynamic rotor may facilitate heat dissipation from the thermally conductive stator vanes. The conductive stator vanes may include thermally conductive stator vanes. The conductive stator vanes may include electrically conductive stator vanes. The electrically conductive stator vanes may provide at least one of power or control signaling to the control unit.

A thrust generator for a rotorcraft includes: a support part detachably mounted to a base provided in the rotorcraft; a rotor shaft rotatably supported by the support part; multiple rotating blades joined to the rotor shaft; and a drive unit detachably mounted to the support part or the base, wherein an output shaft of the drive unit is detachably connected to the rotor shaft.

A thrust generator for a rotorcraft includes: a support part detachably mounted to a base provided in the rotorcraft; a rotor shaft rotatably supported by the support part; multiple rotating blades joined to the rotor shaft; and a drive unit detachably mounted to the support part or the base, wherein an output shaft of the drive unit is detachably connected to the rotor shaft.