Impact Testing and Analysis of Composites for Aircraft Engine Fan CasesSource: Journal of Aerospace Engineering:;2002:;Volume ( 015 ):;issue: 003Author:Gary D. Roberts
,
Duane M. Revilock
,
Wieslaw K. Binienda
,
Walter Z. Nie
,
S. Ben Mackenzie
,
Kevin B. Todd
DOI: 10.1061/(ASCE)0893-1321(2002)15:3(104)Publisher: American Society of Civil Engineers
Abstract: The fan case in a jet engine is a heavy structure because of its size and because of the requirement that it contain a blade released during engine operation. Composite materials offer the potential for reducing the weight of the case. Efficient design, test, and analysis methods are needed to efficiently evaluate the large number of potential composite materials and design concepts. The type of damage expected in a composite case under blade-out conditions was evaluated using a subscale test in which a glass/epoxy composite half-ring target was impacted with a wedge-shaped titanium projectile. Fiber shearing occurred near points of contact between the projectile and target. Delamination and tearing occurred on a larger scale. These damage modes were reproduced in a simpler test in which flat glass/epoxy composites were impacted with a blunt cylindrical projectile. A surface layer of ceramic eliminated fiber shear fracture but did not reduce delamination. Tests on 3D woven carbon/epoxy composites indicated that transverse reinforcement is effective in reducing delamination. A 91-cm (36 in.) diameter full-ring subcomponent was proposed for larger scale testing of these and other composite concepts. Explicit, transient, finite-element analyses indicated that a full-ring test is needed to simulate complete impact dynamics, but simpler tests using smaller ring sections are adequate when the evaluation of initial impact damage is the primary concern.
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contributor author | Gary D. Roberts | |
contributor author | Duane M. Revilock | |
contributor author | Wieslaw K. Binienda | |
contributor author | Walter Z. Nie | |
contributor author | S. Ben Mackenzie | |
contributor author | Kevin B. Todd | |
date accessioned | 2017-05-08T21:16:06Z | |
date available | 2017-05-08T21:16:06Z | |
date copyright | July 2002 | |
date issued | 2002 | |
identifier other | %28asce%290893-1321%282002%2915%3A3%28104%29.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/44963 | |
description abstract | The fan case in a jet engine is a heavy structure because of its size and because of the requirement that it contain a blade released during engine operation. Composite materials offer the potential for reducing the weight of the case. Efficient design, test, and analysis methods are needed to efficiently evaluate the large number of potential composite materials and design concepts. The type of damage expected in a composite case under blade-out conditions was evaluated using a subscale test in which a glass/epoxy composite half-ring target was impacted with a wedge-shaped titanium projectile. Fiber shearing occurred near points of contact between the projectile and target. Delamination and tearing occurred on a larger scale. These damage modes were reproduced in a simpler test in which flat glass/epoxy composites were impacted with a blunt cylindrical projectile. A surface layer of ceramic eliminated fiber shear fracture but did not reduce delamination. Tests on 3D woven carbon/epoxy composites indicated that transverse reinforcement is effective in reducing delamination. A 91-cm (36 in.) diameter full-ring subcomponent was proposed for larger scale testing of these and other composite concepts. Explicit, transient, finite-element analyses indicated that a full-ring test is needed to simulate complete impact dynamics, but simpler tests using smaller ring sections are adequate when the evaluation of initial impact damage is the primary concern. | |
publisher | American Society of Civil Engineers | |
title | Impact Testing and Analysis of Composites for Aircraft Engine Fan Cases | |
type | Journal Paper | |
journal volume | 15 | |
journal issue | 3 | |
journal title | Journal of Aerospace Engineering | |
identifier doi | 10.1061/(ASCE)0893-1321(2002)15:3(104) | |
tree | Journal of Aerospace Engineering:;2002:;Volume ( 015 ):;issue: 003 | |
contenttype | Fulltext |