在SiC/BN/SiC陶矩阵复合航空发动机结构上的氧化驱动损伤:一个代计算框架.
Giacomo Canale1, Roberto Citarella2
1College of Science and Engineering, Nuclear Engineering, University of Derby, Markeaton Street Campus, Derby DE22 3AW, UK.
Materials (Basel, Switzerland)
|June 27, 2024
概括
陶矩阵复合材料 (CMC) 由于其低密度和高温强度,为航空发动机提供了显著的优势. 这项研究模拟了CMC氧化和刚性降解,揭示了对结构完整性至关重要的合现象.
科学领域:
- 材料科学 材料科学 材料科学
- 机械工程 机械工程
- 计算机建模 计算建模
背景情况:
- 陶矩阵复合材料 (CMCs) 是航空发动机中金属合金的有希望的替代品,提供更低的密度和更高的高温性能.
- 然而,关于CMC结构完整性的挑战仍然存在,特别是它们的脆性和易受氧化,这降低了材料性能.
研究的目的:
- 用Fick定律对CMCs的实验氧化数据进行建模和复制.
- 开发一个计算框架来分析CMC中氧气扩散和刚性降解的合现象.
主要方法:
- 在Abaqus中实施Fick的定律模型来模拟氧化过程.
- 开发一个代计算框架,将氧气扩散与刚性降解联系起来.
主要成果:
- 使用菲克定律成功建模了最近的氧化实验数据,为CMCs提供了设计参数.
- 证明氧化诱导的刚性降解和通过微裂变加速的氧气扩散之间的结合关系.
结论:
- 开发的模型和计算框架为设计强大的CMC组件提供了有价值的工具,用于苛刻的应用.
- 了解氧化和机械降解之间的相互作用对于确保航空发动机中CMC的长期结构完整性至关重要.
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