Bending Damage Evolution of Continuous SiC Fiber‐Reinforced Titanium Matrix Composite Panel at High Temperature under Gradient Loading

Continuous SiC fiber‐reinforced titanium matrix (SiC _f /Ti) composites are considered promising candidates for low‐pressure compressor blades of aero engines. However, overload failure under coupling conditions of elevated temperature and bending load is the typical failure mode of blade materials, which is important to understand bending damage evolution at service temperature. Herein, three‐point bending interrupted tests of SiC _f /Ti composite panel are conducted on parallel specimens at 723 K to capture different damage stages. Combining scanning electron microscopy and micro‐computed tomography, together with finite element analysis, is employed to investigate the failure mechanisms. The composite exhibits a bending strength of 1689 MPa at 723 K. The damage evolution follows a sequential process, interfacial debonding (stage I), tensile‐side fiber fracture (stage II), matrix cracking and multiple fiber breaks (stage III), cladding fracture and limited compressive‐side fiber failure (stage IV), and final catastrophic fracture (stage V). Distinct stress states lead to different fracture morphologies on the tensile and compressive sides, with tensile stress identifies as the primary factor governing failure. These findings establish a coherent understanding of the correlation between stress states and bending damage evolution, providing valuable insights for the structural designs and service reliability of SiC _f /Ti composite components in high‐temperature applications.