Safran Aero Boosters Sa

Rafael Perez

Nicolas Raimarckers

Frédéric Vallino

Maxime Dumont

The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.

Aircraft machine part incorporating at least one pressure sensor

Shroud assembly of an axial turbomachine () having a rotor (), such as a turbomachine compressor air-intake shroud (). The assembly comprises an annular layer () of abradable material that is able to cooperate by abrasion with lips () of the turbomachine in order to ensure tightness, and a heating module () for the abradable layer (). The module () comprises electrical heating resistors () within the abradable material in order to prevent the presence of ice on the shroud (). The abradable material is thus used as a heating body which receives, transports and distributes the heat used for de-icing.

De-icing shroud for a compressor of turbomachine

The invention relates to a system of vanes with adjustable orientation, also called a system of variable stator vanes, for a low-pressure compressor of an axial turbine engine. The system comprises vanes, each having a vane extending radially in a flow of the turbine engine and a spindle having a cylindrical portion connected to a telescopic actuating lever. The cylindrical portion comprises radially extending slot, and the actuating lever comprises a pivot joint housed in the slot, that is configured to communicate a rotary movement to the vane about its spindle. The invention also proposes a compressor and a turbine engine.

System of variable stator vanes for a turbine engine

The present application relates to a blade of a rectifier of a low pressure compressor of an axial turbomachine. The blade can also be a rotor and/or turbine blade. The blade includes a composite material with a matrix and a reinforcement comprising a mesh with rods. The rods of the reinforcement are connected to each other and are distributed throughout the volume between the pressure side surface and the suction side surface of the blade. The mesh forms a three-dimensional structure extending over the majority of the thickness of the blade between the pressure side surface and the suction side surface and/or the majority of the length of the blade between the leading edge and the trailing edge. The present application also relates to an iterative method for manufacturing a blade composite where the reinforcement is formed by additive layer manufacturing based on titanium powder and then placed in an injection mold.

Growing community of inventors

Boncelles, Belgium

Rafael Perez