Gouging and Fracture of Engine Containment Structure under Fragment Impact
Publication: Journal of Aerospace Engineering
Volume 21, Issue 3
Abstract
This paper presents a numerical study of the failure response of an aircraft engine containment panel obliquely impacted by a titanium turbine fragment. A three-branch Bao-Wierzbicki fracture criterion is first calibrated for the target material (2219-T851 aluminum alloy) by performing tensile tests on round bars and upsetting tests on short cylinders. With this fracture model, the finite-element simulation of the impact test successfully captures the formation of an indentation/gouging channel on the proximal surface of the panel and the growth of a crack on the distal surface. An extensive parametric study is conducted on the effect of fracture criteria, mesh size, projectile pitch angles, and finite-element codes. Deficiencies of the Johnson-Cook and the constant critical strain fracture model are identified. It is found that the numerically predicted residual thickness and mass loss of the panel are sensitive to the magnitude of the pitch angle of the projectile. A large difference in calculated energy dissipation between ABAQUS and LS-DYNA is observed.
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Acknowledgments
The writers would like to thank Mr. Peter Finnigan and Mr. Gang Qian of the General Electric Global Research Center for providing valuable information on material and loading conditions that was necessary to develop the present model and to verify our numerical solutions. The financial assistance of the GE Global Research Center in the form of an unrestricted gift is greatly appreciated.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 21 • Issue 3 • July 2008
Pages: 174 - 186
Copyright
© 2008 ASCE.
History
Received: Dec 11, 2006
Accepted: Aug 13, 2007
Published online: Jul 1, 2008
Published in print: Jul 2008
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