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Synthesis and analysis of Mo-Si-B based coatings for high temperature oxidation protection of ceramic materials.

机译：用于陶瓷材料高温氧化保护的Mo-Si-B基涂层的合成与分析。

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摘要

The use of Ni-based superalloys in turbine engines has all but been exhausted, with operating temperatures nearing the melting point of these materials. The use of ceramics in turbine engines, particularly ceramic matrix composites such as SiC/C and SiC/SiC, is of interest due to their low density and attractive mechanical properties at elevated temperatures. The same materials are also in consideration for leading edges on hypersonic vehicles. However, SiC-based composites degrade in high temperature environments with low partial pressures of oxygen due to active oxidation, as well as high temperature environments containing water or sand. The need for a protective external coating for SiC-based composites in service is obvious. To date, no coating investigated for SiC/C or SiC/SiC has been proven to be resistant to oxidation and corrosion at intermediate and high temperatures, as well as in environments deficient in oxygen.;The Mo-Si-B coating shows great promise in this area, having been proven resistant to attack from oxidation at extreme temperatures, from water vapor and from calcia-magnesia-aluminosilicate (CMAS). The adaptation of the Mo-Si-B coating for ceramic materials is presented in detail here. Evaluation of the coating under a range of oxidation conditions as well as simulated re-entry conditions confirms the efficacy of the Mo-Si-B based coating as protection from catastrophic failure. The key to the oxidation and corrosion resistance is a robust external aluminoborosilica glass layer that forms and flows quickly to cover the substrate, even under the extreme simulated re-entry conditions.;Suppression of active oxidation of SiC, which may occur during atmospheric re-entry and hypersonic flight trajectories, has also been examined. In order to adapt the Mo-Si-B based coating to low partial pressures of oxygen and elevated temperatures, controlled amounts of Al were added to the Mo-Si-B based coating. The resulting coating decreased the inward diffusion of oxygen with an external Al2O3 layer and effectively reduced the activity of Si in the underlying glass. Thus, the Mo-Si-B based coating is established as a viable protective coating for oxidation and corrosion protection for next-generation aerospace and aeronautical materials.
机译：镍基高温合金在涡轮发动机中的使用已几乎用尽，工作温度接近这些材料的熔点。在涡轮发动机中使用陶瓷，特别是陶瓷基复合材料（例如SiC / C和SiC / SiC），由于其密度低且在高温下具有吸引人的机械性能，因此受到关注。高超声速车辆的前缘也考虑使用相同的材​​料。但是，SiC基复合材料会由于活性氧化而在氧分压低的高温环境中以及含有水或沙的高温环境中降解。在使用中，对于基于SiC的复合材料的保护性外部涂层的需求显而易见。迄今为止，还没有研究证明用于SiC / C或SiC / SiC的涂层在中，高温以及缺氧的环境中具有抗氧化和抗腐蚀的能力; Mo-Si-B涂层具有广阔的前景在该地区，已被证明可以抵抗极端温度下的氧化，水蒸气和氧化钙-镁铝硅酸盐（CMAS）的侵蚀。此处详细介绍了Mo-Si-B涂层对陶瓷材料的适应性。在一定范围的氧化条件以及模拟的再入条件下对涂层进行评估，证实了基于Mo-Si-B的涂层具有预防灾难性失效的功效。抗氧化和抗腐蚀的关键是坚固的外部铝硼硅玻璃层，即使在极端的模拟重入条件下，铝硼硅玻璃层也能迅速形成并流动以覆盖基材。抑制SiC主动氧化，这可能在大气中重新发生进入和高超音速飞行轨迹，也已被检查。为了使基于Mo-Si-B的涂层适应较低的氧气分压和升高的温度，将受控量的Al添加至基于Mo-Si-B的涂层。所得涂层减少了氧气与外部Al2O3层的向内扩散，并有效降低了下方玻璃中Si的活性。因此，基于Mo-Si-B的涂层被确立为用于下一代航空航天材料的抗氧化和防腐保护的可行保护涂层。

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  • 作者

    Ritt, Patrick J.;

  • 作者单位

    The University of Wisconsin - Madison.;

  • 授予单位 The University of Wisconsin - Madison.;
  • 学科 Materials science.
  • 学位 Ph.D.
  • 年度 2015
  • 页码 211 p.
  • 总页数 211
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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