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EI北大核心CSCD

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。

Curing process and thermal stability of polyimide-matrix composite for aero-engines

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 h at 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.