Safran Electrical & Power

Safran Landing Systems

Covidien Ag

Thierry Fontalbat

Florent Challas

Fabien Orlandini

Eric Wissemer

Sylvain Jaber

Nicolas Stefanovic

Jacques Deleris

Quentin Galy

Christophe Cassagnet

Olivier Darnis

Loic Blanco

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

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

The invention relates to an electric centrifugal compressor, in particular for a turbine engine or aircraft, including an electric motor, the stator of which is supported by a casing and the rotor of which includes a shaft mounted inside the casing, driving a centrifugal compressor impeller, the casing having a double skin and including two substantially cylindrical, coaxial skins extending around the engine and defining between them an annular section suitable for the circulation of a first cooling air flow, one inlet of which is located at a first longitudinal end of the shaft and an outlet of which is connected to a second longitudinal end of the shaft, which supports the centrifugal compressor impeller, wherein it includes means (J) for collecting a second air flow at the outlet of the centrifugal compressor impeller, means for channelling the second air flow along the shaft up to the first end, and means for discharging the second air flow out of the casing in order to prevent same from mixing with the first air flow.

Electric centrifugal compressor of a turbine engine or aircraft

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Balgnac, France

Thierry Fontalbat