Techspace Aero S.a.

Safran Aero Boosters Sa

Techspace Aero

Denis Bajusz

Albert Cornet

David Depaepe

Nicolas Raimarckers

Alain Derclaye

Marc Strengnart

Jacques Charlier

Georges Broers

Yves Culot

Nicholas Raimarckers

Antoine Stephany

Bruno Servais

Régis Dupuy

Jérôme Friedel

Cédric Borbouse

A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate.

Integration of an air-liquid heat exchanger on an engine

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

The present invention relates to a method for manufacturing an air/fluid heat exchanger (), said method comprising at least the following steps:

Method for manufacturing a heat exchanger and exchanger obtained by the method

Setting in place of one or several coolers in the wall of a secondary flow of a bypass turbomachine. The wall extends from an intermediate casing toward a leading edge of a separator nose between a primary flow and the secondary flow. The wall includes a series of support arms attached to an intermediate casing, distributed over the perimeter of the wall and directed upstream. A series of surface air-oil heat exchangers forming wall segments are arranged end-to-end on the support arms, so as to form an annular wall. A shroud having a leading edge is arranged and fixed in the area of the upstream edges of the heat exchangers, so as to complete the wall. The support arms include hydraulic connectors connected to one another on each arm, adapted to cooperate with corresponding connectors in the area of the heat exchangers and in the area of the intermediate casing.

Integration of a surface heat exchanger to the wall of an aerodynamic flowpath by a structure of reinforcement rods

The present invention relates to a method for calculating the oil consumption and autonomy associated with the lubrication system of an airplane engine during flights, preferably a turbine engine, on the basis of the measurement of the oil level in the tank of said lubrication system, allowing to manage the refills and maintenance and to detect either abnormal consumption or insufficient autonomy, characterized by at least one of the following methods:

Method for controlling the consumption and for detecting leaks in the lubrication system of a turbine engine

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Remicourt, Belgium

Denis Bajusz