INVESTIGATION OF PARTICLE DEPOSITION AND EROSION CHARACTERISTICS OF AXIAL COMPRESSOR BLADES

This paper presents a numerical simulation study of the erosive and depositional effects of sand and dust particle ingestion within the compressors of aircraft engines, utilizing a gas-solid two-phase flow approach. An Euler-Lagrangian framework is adopted to track individual particles within the flow field, with a focus on the impact of particle parameters on component erosion. The investigation delves into the internal characteristics of erosion and deposition in the compressor, informed by the behavior of the particle trajectories. Findings reveal that an increase in particle size correlates with more erratic particle paths and an intensified erosion of the compressor blades. The impact angle remains relatively unchanged across various particle sizes, indicating that the velocity of impact is the predominant erosive force. Deposition primarily occurs on the leading edge and pressure side of the blades, with total deposition volume escalating with particle diameter. Interestingly, the deposition rate decreases as particle size increases. This study provides insights that are critical for the enhancement of aero-engine design and maintenance protocols.