Evaluation of lightweight material concepts for aircraft turbine engine rotor failure protection
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1997-07-01
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By LE, DY D.
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TRIS Online Accession Number:00880688
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OCLC Number:37656374
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Edition:Final report
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NTL Classification:NTL-AVIATION-Aviation Safety/Airworthiness
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Abstract:Results of the evaluation of lightweight materials for aircraft turbine engine rotor failure protection are presented in this report. The program consisted of two phases. Phase 1 was an evaluation of a group of composite materials which could possibly contain the impact energies of 1.0 x 10 6 inch-pounds generated by T53 rotor fragments. Phase 2 refined system composition and weight of the optimum materials selected from phase 1 and determined their performance under elevated temperatures. Based on the results of phase 1, the aluminum lined fiberglass is the best system, so far. The Aramid system with an aluminum
liner performed almost as effective as aluminum lined fiberglass under ambient conditions. Dry Kevlar performed better than Kevlar impregnated with phenolic resin. Under elevated temperatures, the performances of the aluminum lined fiberglass system, based on energy per weight and thickness, reduced by 50 and 33 percent respectively. An increase of 92 percent in containment ring weight and 304 percent in its thickness is required to compensate for the degradation of the fiberglass system performance under high temperatures. Fabric composite systems absorbed the kinetic energy of fragments through elastic deformation and interlaminated shear of composite layers. Interagency Agreement
DTFA03-95-X-90010 and DTFA03-88-A-00029. Performing Organization Report No. AIR-447200P
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