Explicit Finite Element Modeling of Multilayer Composite Fabric for Gas Turbine Engine Containment Systems, Phase II. Part 4: Model Simulation for Ballistic Tests, Engine Fan Blade-Out, and Generic Engine

摘要

Under the Federal Aviation Administration Airworthiness Assurance Center of Excellence, and with additional support from the Aircraft Catastrophic Failure Prevention program, Honeywell Engines, Systems & Services collaborated with Arizona State University, SRI International, and the National Aeronautics and Space Administration Glenn Research Center to develop a robust, explicit finite element analysis modeling methodology for gas turbine engines containment systems using multilayer composite fabrics. Honeywells role was to simulate impact tests using LS-DYNA to validate the fabric material models (Tasks 1 and 2) and to apply the methodologies developed during this program to two engine fan blade containment analyses (Task 4). This report describes the work performed and the results obtained.