Techspace Aero S.a.

Safran Aero Boosters Sa

Marc Strengnart

Albert Cornet

Nicolas Raimarckers

David Depaepe

Denis Bajusz

Jacques Charlier

Georges Broers

Yves Culot

Nicholas Raimarckers

Antoine Stephany

Beno&icirc;t Marquet

Patrick Hendrick

Frans Breugelmans

The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an 'S' and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.

Gas flow separator with a thermal bridge de-icer

A monitoring method that includes calculating the autonomy of a lubrication system of an airplane engine and also providing for the diagnosis and prognosis of a plurality of problems and breakdowns of the engine and of its lubrication system by means of measurements taken by sensors arranged in the lubrication system. The method further comprises the step of calculating the status of the lubrication system at a given moment and calculating its evolution over time in order to determine the remaining lifetime before a breakdown.

Method for monitoring the oil system of a turbomachine

A process for collecting oxygen-enriched air during a phase of aerobic flight of a space launch for combustion inside at least one cryotechnic rocket engine is provided. The launch rocket comprises at least one turbofan. The turbofan comprises a high-pressure spool comprising a high pressure compressor, a combustion chamber, turbines, and a low-pressure spool surrounding the high-pressure spool. The spools comprise a blower for collecting the external fluid in the form of a main flow and a derived flow. The main flow follows compression, combustion and depressurization in the turbofan engine. The derived flow is separated into oxygen-enriched air and oxygen-depleted air. The oxygen-enriched air is stored for combustion in a rocket engine, while the oxygen-depleted air is ejected.

Process and device for collecting air, and engine associated therewith

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Fize-le-Marsal, Belgium

Marc Strengnart