Abstract: The invention concerns a helicopter ventilation architecture, said helicopter comprising at least two avionics bays (112a, 112b) comprising electronic equipment (116a, 116b) to be ventilated, said architecture comprising, for each avionics bay, an air inlet (120a, 120b) allowing outside air to enter the avionics bay in order to ventilate said avionics bay, and an air outlet (124a, 124b), allowing the air ventilating the avionics bay to exit the avionics bay, characterised in that the ventilation architecture further comprises a mixing chamber (134), connected to the air outlets, configured to receive the air originating from all the avionics bays, at least one air duct (138a, 138b), connected to the mixing chamber and to an outlet (130a, 130b) for discharging the air to the outside, and at least two fans (128a, 128b), arranged and distributed in the air duct or ducts.

Abstract: Fan (16), in particular for an aircraft cooling unit, having a wheel (128) comprising a hub (138) and an annular array of blades (140), a shaft assembly (136) for driving the wheel about an axis (A), and fusible means for connecting the hub of the wheel to the shaft assembly, said fusible connecting means comprising a first mounting sleeve through which the shaft assembly extends and which is surrounded by the hub, and fusible safety elements (174) which extend parallel to the axis (A) and are configured to break and to disengage the wheel from the shaft assembly when said wheel rotates and a driving torque of the wheel transmitted by the shaft assembly exceeds a certain threshold, characterised in that the connecting means comprise a second wearing sleeve (143) which is inserted between the first sleeve and the hub and through which the fusible elements extend, the second sleeve being made of a material which is different from that of the first sleeve and subject to wear by friction and/or by heating if the

Abstract: The invention relates to a fan, in particular for an aircraft cooling unit, comprising a wheel (128) and a shaft line (136) for driving the wheel about an axis (A), said wheel including a hub (138) supporting an annular row of blades (140), and means (142) for connection to said shaft line that are housed inside said hub. The fan is characterized in that the connection means include at least one meltable safety element (158) designed to be broken and to rotationally disengage at least a portion of the connection means from the shaft line when a torque for driving the wheel that is transmitted by the shaft line exceeds a specific threshold.

Abstract: Fan (16), in particular for an aircraft cooling unit, having a wheel (128) comprising a hub (138) and an annular array of blades (140), a shaft assembly (136) for driving the wheel about an axis (A), and fusible means for connecting the hub of the wheel to the shaft assembly, said fusible connecting means comprising a first mounting sleeve through which the shaft assembly extends and which is surrounded by the hub, and fusible safety elements (174) which extend parallel to the axis (A) and are configured to break and to disengage the wheel from the shaft assembly when said wheel rotates and a driving torque of the wheel transmitted by the shaft assembly exceeds a certain threshold, characterised in that the connecting means comprise a second wearing sleeve (143) which is inserted between the first sleeve and the hub and through which the fusible elements extend, the second sleeve being made of a material which is different from that of the first sleeve and subject to wear by friction and/or by heating if the

Abstract: The invention concerns a helicopter ventilation architecture, said helicopter comprising at least two avionics bays (112a, 112b) comprising electronic equipment (116a, 116b) to be ventilated, said architecture comprising, for each avionics bay, an air inlet (120a, 120b) allowing outside air to enter the avionics bay in order to ventilate said avionics bay, and an air outlet (124a, 124b), allowing the air ventilating the avionics bay to exit the avionics bay, characterised in that the ventilation architecture further comprises a mixing chamber (134), connected to the air outlets, configured to receive the air originating from all the avionics bays, at least one air duct (138a, 138b), connected to the mixing chamber and to an outlet (130a, 130b) for discharging the air to the outside, and at least two fans (128a, 128b), arranged and distributed in the air duct or ducts.

Abstract: The invention relates to a fan, in particular for an aircraft cooling unit, comprising a wheel (128) and a shaft line (136) for driving the wheel about an axis (A), said wheel including a hub (138) supporting an annular row of blades (140), and means (142) for connection to said shaft line that are housed inside said hub. The fan is characterized in that the connection means include at least one meltable safety element (158) designed to be broken and to rotationally disengage at least a portion of the connection means from the shaft line when a torque for driving the wheel that is transmitted by the shaft line exceeds a specific threshold.

Abstract: A fan (10) includes: an external ferrule (12), whose internal surface (20) delimits a vein of air (14), a wheel (26) provided with blades (28) rotatably mounted in the ferrule (12) for setting into motion the vein of air, a motor (22) for driving the wheel (26), an electric circuit (40) including components (44) for controlling and powering the motor (22), which circuit (40) includes elements for cooling the components (44) by circulating air taken from the vein of air (14), wherein the cooling elements include a downstream area intake tapping aperture (52) and an upstream tapping aperture (54, 56) for reintroducing air formed through the internal surface (20) of the ferrule (12), and at least one continuous cooling conduit (50) connecting the upstream and downstream tapping apertures isolating the components (44) of the electric circuit from the air circulating in the cooling conduit.

Abstract: A fan (10) includes: an external ferrule (12), whose internal surface (20) delimits a vein of air (14), a wheel (26) provided with blades (28) rotatably mounted in the ferrule (12) for setting into motion the vein of air, a motor (22) for driving the wheel (26), an electric circuit (40) including components (44) for controlling and powering the motor (22), which circuit (40) includes elements for cooling the components (44) by circulating air taken from the vein of air (14), wherein the cooling elements include a downstream area intake tapping aperture (52) and an upstream tapping aperture (54, 56) for reintroducing air formed through the internal surface (20) of the ferrule (12), and at least one continuous cooling conduit (50) connecting the upstream and downstream tapping apertures isolating the components (44) of the electric circuit from the air circulating in the cooling conduit.