Resonance Reliability Analysis of Aeroengine Compressor Rotor Blade

摘要

To describe the frequency distribution of the rotor blades and improve the optimization, resonance reliability of the rotor blades was analyzed in this paper. Considering the variety of random variables, we jointly used finite element method and response surface method. The Campbell diagram was set up to describe blade resonance by analyzing the compressor rotor blade vibration characteristics. For the second-order vibration failure of the rotor blade, we considered the impact of random variables with the rotor blade material, the blade dimension and the rotor speed. The probability distribution and allowable reliability of the second-order vibration frequency was calculated, and the sensitivity of the random variables influencing vibration frequency was completed. The results show that the resonance reliability with the confidence level 0.95 of the rotor blade are R =0.99753 with the excited order k=4 and R =0.99767 with the excited order k=5, and basically agree with the design requirements when the rotor speed n =9916.2 r/min, and the factors mainly affecting the distribution of the second-order vibration frequency of the blades include elastic modulus, density and the rotor speed, with the sensitivity probabilities 35.09%,34.56% and 24.15% respectively.