Safran Aircraft Engines

Ulrich Vincent Max Dubois

Guillaume Julien Puech

Clement Raphael Laroche

Pierre Yves Heinry

Thibaut Michel Lucien Viller

Vincent Fameau

Kevin Emilien Andre Minjot

An assembly for a turbine engine fan case and an air inlet, in particular for an aircraft. The turbine engine extending along a longitudinal axis and comprising at least one fan mounted so as to be rotatable about the longitudinal axis. The fan case comprising at least a first peripheral lining. The first peripheral lining being made of an abradable material configured to be capable of being worn out during the rotation of the fan. The air inlet comprising at least one second peripheral lining. The second peripheral lining being made of an abradable material configured to be capable of being worn out during the rotation of the fan.

Assembly for a turbine engine fan case and an air inlet, method for using such an assembly

The invention relates to a device for simulating the centrifugal acceleration applied to at least one aeronautical turbomachine rotor blade. This device is notable in that it comprises at least one rotor disc () comprising a rim in which there are formed a plurality of pockets () delimited by two lateral teeth () and at least one simulation test () which comprises a screw (), a spacer () and a dummy blade (), in the dummy blade comprises a bore (), which is tapped over at least part of its length and in that the dummy blade, the screw and the spacer are configured and arranged in such a way that when the screw is screwed into the tapped bore, the root () of the dummy blade is engaged in the pocket in the disc, the screw comes into abutment against the spacer and presses same against the two lateral teeth situated one on each side of the pocket in the rotor disc and that this causes the dummy blade to move towards the outside of the disc.

Device for simulating the centrifugal acceleration applied to at least one aeronautical turbomachine rotor blade

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Moissy-Cramayel, France

Ulrich Vincent Max Dubois