Inorganic Fiber Damage Prediction during Textile Yarn Processing

GE航空目前正在开发用于发动机的陶瓷基复合材料（cmc）。这些cmc是由碳化硅（SiC）陶瓷纤维嵌入SiC基体材料制成的。形成纱线的碳化硅陶瓷纤维具有很高的硬度和脆性。在所有的纱线处理过程中（例如，涂纱，绕线等），纱线都会受到中等程度的损坏。这种损害累积起来，对零件质量和产量都有不利影响。这个项目的目标是开发一种模型方法来理解纱线加工过程中纤维的损伤机制。将在Abacus中创建一个参数化非线性准静态有限元模型来表示纱线处理情况。设计并制作了一个由进料纱芯、几个摩擦面和收纱芯组成的小型试验台。该钻机将重现纤维损伤形成机制，并将有助于验证建模方法。摩擦累积量将从建模和测试中确定。该数量将用于解释损伤产生和评估纤维加工设备设计。模型文件和报告将被交付。通过这个项目，我们将开发建模方法来理解纤维-纤维和纤维-表面摩擦相互作用。GE航空Bromont将加大研发力度，将高性能复合材料应用于飞机发动机。

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.