Modeling of Particle Trajectory and Erosion of Large Rotor Blades

Adel Ghenaiet

doi:10.1155/2016/7928347

Abstract

When operating in hostile environments, engines components are facing a serious problem of erosion, leading to a drastic drop in aerodynamic performance and life-cycle. This paper outlines the modeling and simulation of particle trajectory and erosion induced by sand particles. The governing equations of particle dynamics through the moving of large rotor blades are introduced and solved separately from the flow field by using our in-house particle tracking code based on the finite element method. As the locations of impacts are predicted, the erosion is assessed by semiempirical correlations in terms of impact conditions and particle and target surface characteristics. The results of these computations carried out for different concentrations of suspended dust (sand) cloud generated at takeoff conditions reveal the main areas of impacts with high rates of erosion seen over a large strip from the blade suction side, around the leading edge and the pressure side of blade. The assessment of the blade geometry deterioration reveals that the upper corner of blade suffers from an intense erosion wear.

Highlights

Aeroengines manipulating airflows laden by dust or volcanic ash suffer from extreme erosion wear, especially the front components
The air and particles experience different degrees of turning through the rotor blade depending on their sizes
The deviations from air flow paths increase with particle inertia to provoke repeated impacts with the various surfaces of rotor blade

Summary

Introduction

Aeroengines manipulating airflows laden by dust or volcanic ash suffer from extreme erosion wear, especially the front components. The fine particles of dust cloud generated by rotor turning remain suspended for a considerable time, and when the blades move they are continually bombarded by the entrained particles [1] In these circumstances, erosion is often seen on the leading edge as well as the aft of rotor blade body, leading to premature stall and producing a sudden change in torque and a rise in required power [2]. The role of erosion has been well recognized in turbomachinery applications, where the damage is evident in pitting on the blade leading edge and trailing edge and ensues in increased surface roughness [3] In this context, erosion by solid particles and other particulates have shown detrimental effects on the aerodynamics of blades and life-cycle. One of the main effects of deterioration and fault is the modification of compressor and turbine performance maps [4] and subsequently the degradation of engine performance

Methods

Results

Conclusion