The compressor within an aircraft engine is one of its core components, whose primary function is to draw in air and increase its pressure before feeding it to the next stage of the engine’s cycle. The rotor blades, as they rotate at high speeds, continuously accelerate and compress the air, which is the direct method of pressure increase realized by the compressor blades—the performance of the compressor is reflected in the blade design. Addressing the issue of vibration fatigue damage to the rotating blades at work, this study examined the vibration characteristics and causes of damage to compressor blades through finite element analysis. Results indicate that the vibration fatigue damage to the blades arises from the proximity of the excitation frequency to the natural frequency, resulting in resonance and thus blade damage. Therefore, this paper uses finite element analysis software for modeling, followed by static and modal analysis to determine the natural frequencies of the blades, ensuring no resonance phenomena occur within the working frequency range. Furthermore, harmonic response analysis were conducted to further assess the reliability of the blades, providing a basis for the maintenance, fault diagnosis, and design optimization of aircraft engines.