Evaluation of Lightweight Material Concepts for Aircraft Turbine Engine RotorFailure Protection

摘要

Results of the evaluation of lightweight materials for aircraft turbine enginerotor failure protection are presented in the report. Phase 1 was an evaluation of a group of composite materials which could possibly contain the impact energies of 1.0 x 10 to the 6th power 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 precent respectively. Fabric composite systems absorbed the kinetic energy of fragments through elastic deformation and interlaminated shear of composite layers.