航空发动机用聚酰亚胺树脂基复合材料固化工艺及热稳定性能
Curing process and thermal stability of polyimidematrix composite for aero-engines
查看参考文献18篇
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文摘
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针对航空发动机的需求,开展聚酰亚胺树脂基结构复合材料固化工艺与热稳定性评价研究。建立EC-380A树脂的固化动力学方程,模拟树脂固化度随温度和时间的变化。进一步结合树脂流变特性,制定并验证EC-380A复合材料固化成型工艺,制备发动机大尺寸复合材料典型件。通过热老化失重、预置缺陷层合板内部质量和力学性能,评价复合材料的热稳定性。采用330~380℃多温度分级固化的方法,复合材料可整体铺贴无缺陷热压成型。复合材料热稳定性优异,具备370~400℃耐温能力,370℃和285℃累计热老化1000 h,复合材料失重在1.3%左右;400℃热老化后,复合材料无新增缺陷、预置缺陷无扩展,表现出高温结构稳定性。 |
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其他语种文摘
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Aiming at the need of aero-engines,investigation was made into the curing process and thermal stability of a polyimide-matrix structural composite.The curing kinetic equation of EC-380A resin was established.The curing degree of the resin was simulated as a function of the curing temperature and time.Further,combined with the resin rheology,the curing process of the EC-380A composite was established and verified.Large-scaled aero-engine typical structural components were fabricated.Thermal stability of the composite was estimated by mass loss,internal quality of the flaw-embedded laminate,and mechanical property after thermal ageing.By multi-temperature step curing at 330-380 ℃,the flaw-free composite could be manufactured under the circumstance of an integrated layup.The composite has excellent thermal stability with thermal resistance of 370-400℃. The mass loss rate is around 1.3% after ageing for 1000 hat 370 ℃ and 285℃.No new flaw or propagation of the embedded flaw occurs for the composite after thermal ageing at 400℃,indicating a high-temperature structural stability. |
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来源
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材料工程
,2022,50(7):102-109 【核心库】
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DOI
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10.11868/j.issn.1001-4381.2021.001238
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关键词
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航空发动机复合材料
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聚酰亚胺
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固化工艺
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热稳定性
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预置缺陷
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地址
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中国航发北京航空材料研究院软材料技术研究中心, 北京
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先进复合材料国防科技重点实验室, 先进复合材料国防科技重点实验室, 北京
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1001-4381 |
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学科
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航空 |
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基金
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中国科协青年人才托举工程项目
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国家重大科技专项
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文献收藏号
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CSCD:7261529
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