High‐Temperature Alloys in Aeroengines: Damage and Fracture Insights From Micromechanical Modeling

Abstract

ABSTRACT High‐temperature alloys are the cornerstone of aeroengine hot‐section components, where extreme thermomechanical conditions give rise to intricate damage and fracture behaviors that critically limit the structural integrity of whole aeroengines. Generally, Ni‐based superalloys and Ti alloys are commonly used in turbine and compressor blades, whereas high‐entropy alloys, refractory alloys, and TiAl intermetallics are promising candidates. In recent decades, micromechanical models such as crystal plasticity, discrete dislocation plasticity, and molecular dynamics have emerged as powerful tools for unraveling the microstructure‐sensitive crack nucleation and propagation mechanisms. For tackling critical challenges pertaining to high‐temperature alloy design, this work illustrates the utilization of micromechanical modeling to pinpoint latent microstructural characteristics governing failure susceptibility. Building on deepened understanding, micromechanics‐guided strategies for performance optimization are reviewed, including composition design, microstructure regulation, and surface engineering. In particular, metal additive manufacturing enables programmable microstructures and site‐specific properties, offering new opportunities for damage mitigation. This review summarizes micromechanics‐informed damage mechanisms and performance optimization strategies, paving the way for developing next‐generation high‐temperature alloys in aeroengines.