NASA Glenn Research Center, Cleveland, Ohio
A&P Technology, Cincinnati, Ohio
General Aircraft Engines, Cincinnati, Ohio
Cincinnati Testing Laboratories, Cincinnati, Ohio
In an on-going effort to increase the safety and efficiency of turbine engines, the National Aeronautics and Space Administration is exploring lightweight alternatives to the metal containment structures that currently encase commercial jet engines. Epoxy reinforced with braided carbon fibers is a candidate structural material which may be suitable for an engine case. This paper reports flat-coupon mechanical-property experiments performed to compliment previously reported subcomponent impact testing and analytical simulation of containment structures. Triaxial-braid T700/5208 epoxy and triaxial-braid T700/M36 toughened epoxy composites were evaluated. Also, two triaxial-braid architectures (0°,+/-60° and 0°,+/-45°) with the M36 resin were evaluated through tension, compression and shear testing. Tensile behavior was compared between standard straight-sided specimens (ASTM D3039) and bowtie specimens. Both double-notch shear (ASTM D3846) and Iosepescu (ASTM D5379) tests were performed as well. The M36/0°,+/-45° configuration yield the best response when measurements were made parallel to the axial tows. Conversely, the M36/0°,+/-60° configuration was best when measurements were made perpendicular to the axial tows. The results were used to identify critical properties and to augment the analysis of impact experiments.
