Influence of SiO2 and Al2O3 particles on erosion wear of aero-compressor blades

Abstract

When helicopters take off and land in areas such as plateaus and deserts, both SiO2 and Al2O3 particles in the external environment can cause erosion wear on compressor blades, compromising helicopter safety during operation. The aim of this study is a model of a pre-1.5-stage compressor from a turboshaft engine. The experimental schemes of SiO2 and Al2O3 particle velocimetry and Ti–6Al–4V alloy erosion wear were designed to construct a Tabakoff erosion wear model. The influence of particle density and hardness on the erosion rate was deduced. The trajectories and velocities of the two types of particles were analyzed using the gas-solid two-phase flow method. The erosion pattern of the blade was investigated to determine the influence of the two-particle on the erosion rate of the blade. The results showed that Al2O3 particles produced more energy than SiO2 particles and had a higher ability to erosion materials. The maximum impact angle of both the SiO2 and Al2O3 particles on the Ti–6Al–4V alloy was 30°, and the erosion rate of Al2O3 particles at this angle was 66% higher than that of the SiO2 particles. The erosion patterns of the compressor guide, rotor, and stator blades did not vary with the particle material; however, the erosion rate caused by the Al2O3 particles on the blade was larger than that of the SiO2 particles. The maximum erosion rate on the compressor occurred at 98.5% span of the leading edge of the rotor blade, and the erosion rate generated by the Al2O3 particles at this position was 114% higher than that of the SiO2 particles. This research can provide a theoretical reference for anti-erosion protection designs and vibration characteristic analysis of aero-engine compressor blades.