Inorganic Fiber Damage Prediction during Textile Yarn Processing

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GE Aviation is currently developing ceramic matrix composites (CMCs) for engine applications. These CMCsare made with silicon carbide (SiC) ceramic fiber embedded in a SiC matrix material. The SiC ceramic fibersforming the yarns are highly stiff and brittle. During all yarn handling operations (e.g., coating, spooling, etc.),yarns undergo a moderate level of damage. This damage accumulates and has a detrimental effect on both partquality and yield. This project's objective is to develop a modelling approach to understand the fiber damagemechanisms during yarn processing. A parametric non-linear quasi-static finite element model will be createdin Abacus to represent yarn handling situations. A small test rig composed of a feed yarn spool, several frictionsurfaces and a take-up spool be designed and built. The rig will reproduce fiber damage creation mechanismsand will help validate the modelling approach. A friction accumulation quantity will be determined from themodelling and testing. This quantity will be used to explain damage creation and assess fiber processingequipment design. The model files and a report will be delivered. With this project, we will develop modellingapproaches to understand fiber-fiber and fiber-surface friction interactions. GE Aviation Bromont will expandits R&D efforts towards high performance composite applications in aircraft engines.