[en] To investigate the contact phenomenon between the blade
tip and the abradable coated casing, a rig test was designed
and built. This rig test fills the following constraints:
simplification of the low-pressure compressor environment but
realistic mechanical conditions, ability to test several designs
in short time, at low cost and repeatability. The rig test gives
the opportunity to investigate the behavior of different blade
designs regarding the sought phenomenon, to refine and mature
the phenomenon comprehension and to get data for the
numerical tool validation.
The numerical tool considers a 3D finite elements model of
low-pressure compressor blades with a surrounding rigid
casing combined with a specialized model to take into account
the effects of the wear of the abradable coating on the blade
dynamics. Numerical results are in good agreement with tests
in terms of: critical angular speed, blade dynamics and wear
pattern on the abradable coated casing
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Pacyna, Laura; Safran Aero Boosters
Bertret, Alexandre; Safran Aero Boosters
Derclaye, Alain; Safran Aero Boosters
Papeleux, Luc ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > LTAS-Mécanique numérique non linéaire
Ponthot, Jean-Philippe ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > LTAS-Mécanique numérique non linéaire
Language :
English
Title :
IMPLEMENTATION OF A RIG TEST FOR ROTOR/STATOR INTERACTION OF LOWPRESSURE COMPRESSOR BLADES AND COMPARISON OF EXPERIMENTAL RESULTS WITH NUMERICAL MODEL
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