Fatigue analysis of compressor blade with simulated foreign object damage

• Experimental investigation was used for fatigue analysis of the compressor blade.
• The compressor blade with V-notch created by machining was investigated.
• First mode of transverse vibration with constant amplitude was considered.
• Both the number of load cycles for crack initiation and also the crack growth dynamic were obtained.
• FEM analysis was additionally made for stress determination in vibrated blade.

In this work the fatigue analysis of aero engine compressor blade subjected to resonant vibration was performed. In experimental investigations the blade with V-notch which simulates the foreign object damage (FOD) was considered. The notch located on the leading edge of the blade was created by machining. Mechanical defect (FOD) causes a considerable decrease of the fatigue life of blade working in resonance conditions. The main assumption of experimental investigations was to maintain the constant vibration amplitude during the blade fracture. As a result of performed investigations both the number of load cycles to crack initiation and also the crack growth dynamics were determined. In the last part of the work the finite element method (FEM) was used in order to determine the stress field in the blade with V-notch, subjected to resonant vibration.