Safran Electrical & Power

Safran Landing Systems

Florent Challas

Thierry Fontalbat

Fabien Orlandini

Sylvain Jaber

Christophe Castelli

Fabien Del Rio

Eric Wissemer

Quentin Galy

Christophe Cassagnet

Jean Manel-Delaleux

Loic Blanco

Jean Manel- De - Laleux

A system for cooling the brakes of a brake system of a landing gear of an aircraft, including: a compressor configured to generate a pressurized airflow, the compressor including at least one air outlet, and an air jet pump including: a pump tube including a first end connected to the air outlet and a second end, the pump tube being designed to carry the pressurized airflow between the first and second ends, and a plurality of injectors connected to the second end of the pump tube, and configured to inject the pressurized airflow.

System and method for cooling the brakes of landing gear of an aircraft

Aircraft landing gears include at least one wheel, an electric taxiing system including an electric taxiing motor, brakes capable of slowing down or stopping the rotation of the wheel, and a cooling system for cooling the electric taxiing motor and the brakes. The cooling system includes ventilation means capable of mixing a first air flow originating from the brakes and a second air flow originating from outside the landing gear and of ventilating the electric taxiing motor with a mixture of the two air flows.

Landing gear of an aircraft and method for cooling an electric taxiing motor and brakes of such a landing gear

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

Helicopter ventilation architecture with mixing chamber

A helicopter turbomachine includes an electric starter motor configured to rotate a drive shaft, a heat sink for cooling the electric motor, and a reversible ventilation wheel driven by the electric motor. The turbomachine also includes an overrunning clutch that transmits the torque from the electric motor to the drive shaft. The electric motor is configured such that, in the first direction of rotation, the motor rotates the drive shaft and the ventilation wheel to generate an air flow through the heat sink in a direct direction, and, in the reverse direction of rotation, the motor rotates only the ventilation wheel to generate an air flow through the heat sink in a direction opposite the direct direction.

Turbine engine with starter motor with reversible ventilation, and associated cooling method

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Blagnac, France

Florent Challas