Safran Aircraft Engines

Paco Maurer

Julien Fabien Patrick Becoulet

Antoine Jean-Philippe Beaujard

Serge Rene Morreale

Serge René Morreale

Fabien Roger Gaston Caty

Nicolas Stoliaroff-Pepin

Mathieu Jean Pierre Trohel

Maeva Daphné Gros-Borot

A turbomachine includes a low-pressure shaft having an internal passage for a first air stream and a first segment. A second segment includes a first frustoconical portion, and an intermediate lubrication chamber wherein at least one bearing is arranged. The intermediate lubrication chamber is arranged in an intermediate casing. An annular air chamber is configured to be supplied with air from a low-pressure compressor and is at least partly axially delimited by the first frustoconical portion. A radial separating wall is mounted around the first segment, and the first frustoconical portion further includes an opening to enable the first air stream to pass from the air chamber to the internal passage.

Turbomachine for an aircraft

A scoop for an aircraft turbine engine, this scoop including a body which is movable between at least two positions, including a first position in which it is configured to capture part of a first air stream flowing in a first direction, wherein the body is movable into a second position in which it is configured to capture part of a second air stream flowing in a second direction which is opposite to the first direction, and wherein the body is mounted to move freely between the at least two positions so as to automatically adopt the first position when the first air stream flows, and to automatically adopt the second position when the second air stream flows.

Scoop for an aircraft turbine engine

A turbo machine including a device for ventilating and pressurising a turbine rotor of a turbomachine having an axis, the device including at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber inside the turbomachine that communicates with a second inner chamber delimited by the turbine rotor, the first and second chambers being at least partially separated by a stationary shroud having the axis, wherein it includes at least one injector passing through the stationary shroud and having a cross-section that varies in response to a pressure difference between the first and second chambers.

Turbomachine with device for cooling and pressurising a turbine

A ventilated chamber (), subject to an irruption of air at a pressure higher than that in a surrounding chamber () through labyrinth seals separating them and evacuation of excess air through an evacuation duct (), comprises a motor-driven compressor () in the evacuation duct to facilitate suction and evacuation, even when the engine speed does not allow a large overpressure in the chamber ().

Device for evacuation of a ventilated lubricated chamber of a turbomachine

In order to compensate for the increase in a leakage rate of ventilation air originating in a circuit via a labyrinth seal that gradually wears at the bottom of a ventilation chamber, and the reduction of a purge rate via an opening upstream from the chamber, a second injection opening is added to a main injection opening. The second injection opening communicates with the chamber via a second labyrinth seal that wears at the same time as the first, and thus gradually increases the air flow rate passing through the injector in order to compensate for the additional leakage rate through the first injector and maintain the ventilation at its initial level.

Growing community of inventors

Moissy-Cramayel, France

Paco Maurer