J. Phys. IV France
Volume 134, August 2006
EURODYMAT 2006 - 8th International Conference on Mechanical and Physical Behaviour of Materials under Dynamic Loading
Page(s) 409 - 415
Publié en ligne 26 juillet 2006
EURODYMAT 2006 - 8th International Conference on Mehanical and Physical Behaviour of Materials under Dynamic Loading
J. Cirne, R. Dormeval, et al.
J. Phys. IV France 134 (2006) 409-415

DOI: 10.1051/jp4:2006134063

Composite blade damaging under impact

T. Menouillard1, 2, J. Réthoré3, H. Bung2 and A. Suffis4

1  LAMCOS, INSA Lyon, 18 rue des Sciences, 69621 Villeurbanne, France
2  CEA Saclay, DEN/DM2S/SEMT/DYN, 91191 Gif-sur-Yvette, France
3  Faculty of Aerospace Engineering, Delft University of Technology, 2600 GB Delft, The Netherlands
4  SNECMA, W/YKM3, Rond point René Ravaud, 77550 Moissy-Cramayel Cedex, France

Published online: 26 July 2006

Composites materials are now being used in primary aircraft structures, and other domains because of numerous advantages. A part of a continuous in-flight operating costs, gas turbine engine manufacturers are always looking for ways to decrease engine weight. This is the case of compressor blades which have to satisfy, for example, the standard bird strike or debris in order to measure the crashworthiness. Bird strike impacts are actually among the most challenging loads that composite blades must accommodate. Thus for the further development of composite structures, it becomes important to have available predictive tools for simulating the response of composite structures under crash or impact loads, which will allow to evaluate damage state in the structure in function of time. A composites damage model, without mesh dependency, is presented, and allows to obtain agreement with impact experiment. Examples of finite element simulations for the impact response of blade based on this materials model are developped. These numerical results correspond to a bird strike on an equivalent composites blade, and insists on damage evolution in structure.

© EDP Sciences 2006