Parametric Study on Failure Mode of the Bearing Support under FBO Load

DOI

10.2991/mseee-17.2017.84How to use a DOI?

Keywords

Aero-engine, FBO, primary fuse, Finite element method.

Abstract

A typical high bypass ratio turbofan engine is used in this paper to study the structural parameters for the fuse, and a hollow thin section on the support of bearing No.1 between a forward bearing seat and an aft mount flange is referred to as the primary fuse structure. Influences of its structural parameters on failure mode of the bearing support under FBO load are discussed based on the explicit dynamic finite element method. As the result of parametric study, the following conclusions are obtained. Shear buckling failure of the bearing support is easy to occur under FBO load when the thin section is near to the front flange. And axial buckling failure of the bearing support is easy to occur when the thin section is near to the rear flange. Thickness of the thin section is directly related to the FBO peak load at the No.1 bearing. Plastic deformation in the form of wrinkling circumferentially around the thin section is observed when the axial width of the thin section is substantially greater than its wall thickness.

Copyright

© 2017, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

Download article (PDF)

TY  - CONF
AU  - Zhimei Zhao
AU  - Huiying Song
AU  - Zhennan Tang
PY  - 2017/08
DA  - 2017/08
TI  - Parametric Study on Failure Mode of the Bearing Support under FBO Load
BT  - Proceedings of the 2017 International Conference on Material Science, Energy and Environmental Engineering (MSEEE 2017)
PB  - Atlantis Press
SP  - 455
EP  - 462
SN  - 2352-5401
UR  - https://doi.org/10.2991/mseee-17.2017.84
DO  - 10.2991/mseee-17.2017.84
ID  - Zhao2017/08
ER  -