Inorganic Fiber Damage Prediction during Textile Yarn Processing

GE航空目前正在开发用于发动机应用的陶瓷基复合材料（CMC）。这些CMC由嵌入SiC基质材料中的碳化硅（SiC）陶瓷纤维制成。形成纱线的SiC陶瓷纤维是高度刚性和脆性的。在所有纱线处理操作（例如，涂布、卷绕等），纱线受到中等程度的损伤。这种损伤累积起来，对零件质量和成品率都有不利影响。本项目的目标是开发一种建模方法，以了解纱线加工过程中的纤维损伤机制。一个参数化的非线性准静态有限元模型将被建立在Abacus中，以代表纱线处理的情况。设计并搭建了一个由喂纱轴、摩擦面和卷取轴组成的小型试验台。该装置将再现纤维损伤产生机制，并将有助于验证建模方法。摩擦累积量将由模型和试验确定。这个数量将被用来解释损伤的产生和评估纤维加工设备的设计。模型文件和报告将被提交。通过这个项目，我们将开发建模方法来理解纤维与纤维和纤维表面摩擦相互作用。通用电气航空布罗蒙特公司将扩大其研发工作，在飞机发动机的高性能复合材料应用。

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.