Factors influencing creep life and deformation mechanisms in Ni-based single crystal superalloys: A review

As a core component of aero engines, the creep life of turbine blade hot-end parts has become a critical technical bottleneck restricting the comprehensive service performance of advanced aero engines. Ni-based single crystal superalloys (SCs), renowned for their high-temperature strength and excellent creep resistance, are the material of choice for turbine blades. During service, creep damage caused by centrifugal stress is the primary failure mode, making the development of Ni-based SCs with enhanced high-temperature creep resistance imperative. However, with each successive generation of Ni-based SCs, the incremental improvement in temperature capability diminishes and their operational temperatures now approach the material's solidus temperature. This study investigates the effects of alloy composition optimization and crystallographic orientation on the high-temperature creep resistance of Ni-based SCs, while elucidating the three-stage creep mechanisms. By tailoring alloy composition and crystallographic orientation, significant enhancements in creep resistance can be achieved. Our findings provide theoretical insights into improving creep resistance in Ni-based SCs and highlight the future potential of advanced creep life prediction methods, such as machine learning, in advancing the durability of aerospace materials. This research contributes to elevating the reliability and service life of turbine blades and other critical engine components.