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The paper presents a failure case of an aero-engine combustor liner. Macroscopic and microscopic observations, microstructure investigation, chemical analysis and hardness measurement have been performed to investigate the damage mechanism and failure causes of notches and cracks. The results show that the failure modes of notches, axial-direction crack along the combustor liner and crack at the edge of welding spot are respectively attributed to high-temperature ablation, mixed crack of ablation and thermal fatigue crack. The bad configuration of crossover tube is the main reason for the failure of combustor liner.

The paper presents a failure analysis of components damaged in compressor vane. In order to investigate the damage mechanism and failure causes of components, macroscopic and microscopic observations, microstructural investigations, chemical analysis and hardness measurement have been performed. The results show that the damaged components are caused by fractured blades of 1st stage rotor. In all 1st stage rotor blades, 1 # blade is fractured firstly, and is troublemaker in this incident. The fracture mechanism of 1 # blade fractured from blade root is due to first order bending vibration fatigue damage. The microstructure, hardness and chemical compositions of 1 # blade fracture, all which coincide with technical requirements. The bad shot peening qualities in the surface near blade fracture have important influence on fatigue failure.