Advanced Joining of Single Crystal Aerospace Materials

对改进的燃气涡轮机发动机效率的不断增长的需求已经驱动了更高的操作温度，导致使用耐热单晶（SX）Ni基超合金和Ni 3Al基金属间化合物来制造航空发动机涡轮机部件。连接不仅对于复杂形状的发动机部件的制造至关重要，而且对于维修和翻新服务损坏的部件也至关重要。然而，SX Ni基高温合金和SX Ni 3Al基金属间化合物由于其对焊接裂纹的高敏感性而极难通过常规熔焊工艺连接。替代的先进技术，如瞬时液相（TLP）焊接保持连接这些材料的潜力，而不会出现开裂的问题。不幸的是，TLP连接的商业应用目前受到限制，主要是由于在多组分基体-填料合金系统的连接过程中对微观结构发展的理解不足。拟议的研究旨在推进TLP连接的工业应用。 申请人提出使用电子显微镜和光谱技术以及数值建模来详细系统地研究减少处理时间的新的有效方法，所述处理时间是在使用多组分商业填充合金的情况下在类似和不同SX材料中产生无杂散晶粒的TLP接头所需的。此外，他和他的团队将开发键合后热处理方案，以使TLP键合材料在化学和微观结构上均匀化，从而改善高温性能。这项研究将大大推进目前对TLP连接机制的理解，并为有效建模和优化连接过程提供有价值的知识。最终，该研究将有助于开发更高效、更可靠的先进SX航空航天材料连接程序，从而增强加拿大在先进连接技术领域的竞争力。

The ever-increasing demand for improved gas turbine engine efficiency has driven operating temperatures higher, leading to the use of heat resistant single crystal (SX) Ni-base superalloys and Ni3Al-base intermetallics to manufacture aero-engine turbine components. Joining is not only essential for the fabrication of complex shaped engine components, but it is also crucial for the repair and refurbishment of service-damaged parts. SX Ni-base superalloys and SX Ni3Al-base intermetallics are, however, extremely difficult to join by conventional fusion welding processes due to their high susceptibility to weld cracking. Alternate advanced techniques such as transient-liquid-phase (TLP) bonding hold potential for joining these materials without the problem of cracking. Unfortunately, the commercial use of TLP bonding is currently limited largely due to the inadequate understanding of microstructural development during the bonding of multi-component base-filler alloy systems. The proposed research is aimed at advancing industrial applications of TLP bonding. The applicant proposes to use electron microscopy and spectroscopy techniques and numerical modeling to systematically study, in detail, new effective ways of reducing the processing time that is required to produce stray-grains-free TLP joint in similar and dissimilar SX materials, with the use of multi-component commercial filler alloys. Furthermore, he and his team will develop post-bond thermal treatment scheme to chemically and microstructurally homogenize TLP bonded materials for improved high-temperature properties. The proposed study will significantly advance the current understanding of TLP bonding mechanisms, and provide valuable knowledge vital to effective modeling and optimization of the joining process. Ultimately, the research will contribute to the development of more efficient and reliable procedures for joining advanced SX aerospace materials, thereby enhancing Canada's competitiveness in pioneering advanced joining technology.