Abstract
To evaluate the effect of the compressor rotor blade on compressor blade fatigue, a non-contact dynamic stress measurement scheme of one aero-engine eighth stage compressor rotor blade was designed, and the dynamic stress test was carried out. Meanwhile, modal analysis of the eighth stage compressor rotor blade was done by finite element analysis software. Results show that between the range of the idle speed and the highest speed, there is no resonance for the eighth stage compressor rotor blade and the maximum vibration amplitude is less than 65 μm, which cannot result in high cycle fatigue failure.
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