Effects of Solid Particle Ingestion Through an HP Turbine

Ghenaiet, Adel

doi:10.1115/gt2012-69875

Cited by 10 publications

(10 citation statements)

References 19 publications

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“…Indeed, high equivalent erosion rates of 24.23 mg/g/mm 2 are found near the trailing edge from pressure side, as attributed to the crowd of particles inducing high frequency of impacts at high velocities. Almost similar erosion pattern for this 1 st NGV was discussed by Ghenaiet in an early paper [8].…”

Section: Suction Sidesupporting

confidence: 82%

“…In addition, there is a region of erosion covering almost the trailing edge, with a spotted corner of equivalent erosion rate of 60.9 mg/g/mm 2 , revealing a rounding shaped wear. Further erosion details are similar to a single stage axial, Ghenaiet [8].…”

Section: Suction Sidementioning

confidence: 89%

“…All these forces and many other effects on particles such as the motion of a particle normal and parallel in vicinity of a wall, that result in an increase of drag and a transverse lift force, are included in the present tracking code. All these details are available in a previous paper (Ghenaiet [8]). For small Reynolds Numbers (Re<0.5) viscous effects are dominating and no separation is observed, this is referred as the Stokes regime (C D =24/Re).…”

Section: Particle Trajectory Computationmentioning

confidence: 99%

“…Tabakoff et al [7] have compared the computed particle trajectories through a two stages turbine and the associated blade erosion, and their results indicate non uniform particles impacts spreading over most of the blade surfaces, and particle size has a significant influence on erosion intensity and pattern. The simulations carried out by Ghenaiet [8] for a one-stage hp axial turbine showed that the whole of NGV pressure surface is subjected to impacts and higher erosion rates are seen beyond the throat. The particle trajectories show that the impacts on the aft part of NGV lead to a significant variations in particles incidence at the entry of rotor blade.…”

Section: Introductionmentioning

confidence: 99%

“…This paper presents the results of a numerical study for the particle dynamics and erosion into two stages of an hp axial gas turbine. The 3D particle trajectory and erosion computations are based on our in-house Lagrangian -finite element tracking code [8][9][10]. This code is now improved to deal with multi-components turbomachinery, as the blade pitch differs from one row to another and there are different angular positions of vanes and blades, which require a complex procedure to deal with particles crossing each interface.…”

Section: Introductionmentioning

confidence: 99%

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Study of Particle Ingestion Through Two-Stage Gas Turbine

Ghenaiet

2014

Volume 2C: Turbomachinery

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This paper presents a numerical study of particle laden gas flow through a two-stage hp axial turbine, by means of an inhouse code based on the Lagrangian tracking model and the finite element method. As fly-ash solid particles trajectories and locations of impacts are predicted, the local erosion rates and the deteriorations of blades are assessed. The computed trajectories provide a detailed description of particles behaviors and reveal that particle impacts on the aft of vane pressure side usually lead to significant variations in the directions of particles to the next rotor blade, and subsequently particles impact the suction side. The plots of equivalent erosion rates indicate the vanes and blades locations which suffer more erosion. The first vane pressure surface is impacted more than any other component, but higher rates are seen at the top corner from trailing edge. The critical regions of erosion wear in the first rotor are observed over the top of blade leading edge extending along the tip as well as a rounding of the top corner from trailing edge. In the second vane, the regions of higher erosion are revealed over the last third of leading edge and the top corner extending along tip. The erosion in the second rotor is over a large area of suction side till the tip corner. The predicted areas of extreme erosion, also shown by the deteriorated profiles, are indicators for anticipated vanes and blades failures. NOMENCLATUREFluid velocity [m/s] Particle velocity [m/s] z Axial coordinate [m] Greek letters β Impact angle [degree] ε Erosion rate [mg/g] Ε q Equivalent erosion rate [mg/s.mm 2 ] & [mg/g.mm 2 ] ρ Density [kg/m 3 ] ω Speed of rotation [rad/s] θ Angular coordinate [rad]

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Section: Suction Sidesupporting

confidence: 82%

Section: Suction Sidementioning

confidence: 89%

Section: Particle Trajectory Computationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Study of Particle Ingestion Through Two-Stage Gas Turbine

Ghenaiet

2014

Volume 2C: Turbomachinery

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Simulation of particle-laden flows and erosion in an axial fan stage considering the relative position of the blades

Ghenaiet

2024

Aeronaut. j.

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Axial fans are vital accessories in aircraft ventilation systems, but, they may experience erosion from particulate flows, causing a decline in effectiveness over time. This study investigated the trajectories of two types of sand particles and erosion in an axial fan stage, considering the relative position of the blades facing the inlet guide vanes. The movement of particles was simulated using an in-house code that implements a Lagrangian approach along with a stochastic particle-eddy interaction model. The flow field was solved separately and the flow data was transferred to the particle trajectory code. The finite element method allowed for the tracking of particles through the computational cells and accurate determination of their impact positions. A semi-empirical erosion correlation was used to evaluate the local erosion rates, mass removal, and geometry deterioration. As a result, the rotor exhibits a high frequency of impacts and significant erosion on the leading edge of the blade, extending to the upper corner of the pressure side and blade tip, as well as the front of the suction side. In the inlet guide vane, the erosion is spread out along the entire pressure side but at lower erosion rates compared to the rotor blade. The erosion patterns obtained at different pitch-wise positions were cumulated to get better representation of erosion patterns. After being exposed to MIL-E5007E sand (0–1000 $\unicode{x03BC}$ m) at the highest concentration for 10 hours, the blade experienced a reduction of a 0.29% in mass, a 0.45% decrease in tip chord, and a 0.23% increase in tip clearance. On the other hand, AC-coarse sand (0–200 μm) resulted in a 0.23% decrease in blade mass, a 0.4% reduction in tip chord, and a 0.16% increase in tip clearance. The data that is available can be used to monitor the lifespan of axial fans of similar design and select appropriate coatings to protect against erosion.

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A numerical study of volcanic ash ingestion and erosion of the front components of a high bypass turbofan engine

Ghenaiet

2024

Aeronaut. j.

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Airborne particles, such as dust and volcanic ash, pose a serious hazard to aircraft in flight due to their potential to cause erosion damage to engine components. It is crucial to anticipate and address the impact of erosion wear on engine performance and safety. This study aims to enhance our understanding of how volcanic ash particles behave when ingested through a high bypass turbofan engine (HBTFE) and assess the development of erosion wear in the front components. The effects of four different ash samples are assessed in various scenarios of encountering volcanic ash during cruise flight conditions. First, the flow solution is obtained for all front components, including the Pitot intake, spinner, fan, inlet guide vanes (IGVs), outlet guide vanes (OGVs), and connecting ducts. Based on the flow data, the particle motion equations are solved step by step using an in-house trajectory and erosion code. This latter adopts the Lagrangian approach, which incorporates a particle-eddy interaction model and includes probabilistic descriptions for the release positions of particles, sizes, and restitution factors. The finite element method (FEM) is used to track particles through the computational cells and determine impact positions and conditions. As a result, the Pitot intake design seems to prevent many ash particles from reaching the fan blade beyond 80% of the span. The fan blade leading edge (LE) exhibits extreme erosion on both sides. The blade’s pressure side (PS) displays erosion spreading practically on the entirety of the surface, especially near the trailing edge (TE). In contrast, the suction side (SS) has scattered erosion at lower rates. Furthermore, the rotor’s hub presents almost uniform erosion patterns, whereas the shroud depicts scattered erosion. This large fan appears to function as a separator, expelling a significant amount of ash particles through the secondary duct, thereby reducing the engine core’s susceptibility to erosion. Out of the four volcanic ash samples, those from the Kelud and Etna volcanoes appear to cause the highest hourly eroded mass, about twice as much as the samples from the Chaiten and Eyjafjallajokull volcanoes.

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Effects of Solid Particle Ingestion Through an HP Turbine

Cited by 10 publications

References 19 publications

Study of Particle Ingestion Through Two-Stage Gas Turbine

Study of Particle Ingestion Through Two-Stage Gas Turbine

Simulation of particle-laden flows and erosion in an axial fan stage considering the relative position of the blades

A numerical study of volcanic ash ingestion and erosion of the front components of a high bypass turbofan engine

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