An aircraft turbine engine includes a gas generator and a fan arranged upstream from the gas generator and configured to generate a main gas flow, one portion of which flows in a flow path of the gas generator to form a primary flow, and another portion of which flows in a flow path around the gas generator to form a secondary flow. The gas generator includes a low-pressure compressor that includes a rotor driving the fan. The turbine engine further includes an electric machine. The electric machine includes a rotor rotated by the rotor of the low-pressure compressor, and a stator extending around the rotor of the electric machine and configured to be cooled by the primary flow.

An aircraft turbine engine includes a gas generator and a fan arranged upstream from the gas generator and configured to generate a main gas flow, one portion of which flows in a flow path of the gas generator to form a primary flow, and another portion of which flows in a flow path around the gas generator to form a secondary flow. The gas generator includes a low-pressure compressor that includes a rotor driving the fan. The turbine engine further includes an electric machine. The electric machine includes a rotor rotated by the rotor of the low-pressure compressor, and a stator extending around the rotor of the electric machine and configured to be cooled by the primary flow.

A motor is provided. The motor includes a cooling system configured to cool a stator having a core wound around by a coil, wherein the cooling system includes oil holders installed on a side under the stator in an inner space of a motor housing and provided to allow oil to be collected up to a level capable of allowing at least some of a lower end section of the stator to be immersed for cooling.

A rotating machine assembly includes a rotating machine that has a cover that defines an outer surface of the rotating machine and a stator disposed within the cover. The stator is stationary with respect to the cover. The rotating machine also includes a shaft rotatably disposed at least partially within the cover so as to define a rotation axis. The shaft Includes a first end that is connectable to an aircraft engine and a second end that is opposite the first end. The rotating machine also includes a rotor attached to the shaft, the rotor being movable with respect to the stator and a power module including at least one MOSFET that periodically reverses an electrical current direction of the rotor. The power module includes the at least one MOSFET Is disposed within the cover.

A fan-equipped motor includes: a motor for rotating a spindle, the motor including a hollow-shaped motor shaft in which a through hole is formed; and a fan for cooling the motor, the fan including a hollow-shaped rotary shaft in which a through hole is formed, and a plurality of blades attached to the rotary shaft, the fan being disposed on the side of the motor that is opposite to the spindle. The motor shaft and the rotary shaft are disposed so that cooling air produced by the fan flows in a different passage and in a different direction from a gas supplied into the through hole of the rotary shaft and flowing in the through hole of the motor shaft.

A fan-equipped motor includes: a motor for rotating a spindle, the motor including a hollow-shaped motor shaft in which a through hole is formed; and a fan for cooling the motor, the fan including a hollow-shaped rotary shaft in which a through hole is formed, and a plurality of blades attached to the rotary shaft, the fan being disposed on the side of the motor that is opposite to the spindle. The motor shaft and the rotary shaft are disposed so that cooling air produced by the fan flows in a different passage and in a different direction from a gas supplied into the through hole of the rotary shaft and flowing in the through hole of the motor shaft.

A motor assembly for powering a fluid blower includes a stator, a rotor rotatable relative to the stator about an axis of rotation, and an inner shell. The inner shell includes axially opposite first and second shell ends and encloses, at least in part, the stator and the rotor. An outer housing at least partly surrounds the inner shell such that an axially extending fluid channel is defined between the inner shell and the outer housing. A motor controller is positioned within the outer housing and is configured to control at least one operational parameter of the motor assembly. Furthermore, the motor assembly includes a flow-directing endshield located within the outer housing and adjacent the first shell end. The rotor is supported, at least in part, by the flow-directing endshield. The flow-directing endshield is fluidly interposed between the fluid channel and motor controller and is configured to direct a fluid flow between the fluid channel and the motor controller.

A motorised respiratory assistance device with an integrated cooling system including an enclosure (1) forming a compartment (2) accommodating a motor unit (3) driving turbines (8a, 8b) generating a main respiratory assistance air flow (F1) and a secondary air flow (F2) for cooling the motor (5). The secondary air flow (F2) is conveyed by a secondary aeraulic path (E2, E4, E5, 22, E3, S2) that includes an inner portion (E2, E4, E5, 22) extending into the motor (5) between the stator (6a) and the rotor (6b) and an outer portion (E3, S2) that extends into an annular space (E3) provided around the motor unit (3). The cooling air flow (F2) flows in opposing directions in the inner (E4) and outer (E3) portions, and the main aeraulic path (E1, E6, S1) and the secondary aeraulic path (E2, E4, E5, 22, E3, S2) are separated from each other by a partition (18).

A motorised respiratory assistance device with an integrated cooling system including an enclosure (1) forming a compartment (2) accommodating a motor unit (3) driving turbines (8a, 8b) generating a main respiratory assistance air flow (F1) and a secondary air flow (F2) for cooling the motor (5). The secondary air flow (F2) is conveyed by a secondary aeraulic path (E2, E4, E5, 22, E3, S2) that includes an inner portion (E2, E4, E5, 22) extending into the motor (5) between the stator (6a) and the rotor (6b) and an outer portion (E3, S2) that extends into an annular space (E3) provided around the motor unit (3). The cooling air flow (F2) flows in opposing directions in the inner (E4) and outer (E3) portions, and the main aeraulic path (E1, E6, S1) and the secondary aeraulic path (E2, E4, E5, 22, E3, S2) are separated from each other by a partition (18).

Provided is an electric tool in which the risk of short-circuiting between conductive members of multiple installed switching elements has been reduced by providing partitioning plates between the switching elements. An electric tool, which has a motor, an inverter circuit with multiple switching elements for performing switching operations and controlling the driving of the motor, a control unit for controlling switching element on-off operations, and a circuit board on which the switching elements are loaded, is configured so that the circuit board is housed inside a container-shaped case (40) and the circuit board is secured with a partitioning member (50) that is interposed between the multiple switching elements and has partitioning plates (51, 52a, 52b) obtained from an insulating material.