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Unsteady simulations of migration and deposition of fly-ash particles in the first-stage turbine of an aero-engine

Published online by Cambridge University Press:  12 April 2021

Z. Hao ,
X. Yang Open the ORCID record for X. Yang [Opens in a new window]  and
Z. Feng
Z. Hao
Affiliation:
Institute of Turbomachinery School of Energy and Power Engineering Xi’an Jiaotong University Xi’an, Shanxi China
X. Yang*
Affiliation:
Institute of Turbomachinery School of Energy and Power Engineering Xi’an Jiaotong University Xi’an, Shanxi China
Z. Feng
Affiliation:
Institute of Turbomachinery School of Energy and Power Engineering Xi’an Jiaotong University Xi’an, Shanxi China
*
x.yang@mail.xjtu.edu.cn
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Abstract

Particulate deposits in aero-engine turbines change the profile of blades, increase the blade surface roughness and block internal cooling channels and film cooling holes, which generally leads to the degradation of aerodynamic and cooling performance. To reveal particle deposition effects in the turbine, unsteady simulations were performed by investigating the migration patterns and deposition characteristics of the particle contaminant in a one-stage, high-pressure turbine of an aero-engine. Two typical operating conditions of the aero-engine, i.e. high-temperature take-off and economic cruise, were discussed, and the effects of particle size on the migration and deposition of fly-ash particles were demonstrated. A critical velocity model was applied to predict particle deposition. Comparisons between the stator and rotor were made by presenting the concentration and trajectory of the particles and the resulting deposition patterns on the aerofoil surfaces. Results show that the migration and deposition of the particles in the stator passage is dominated by the flow characteristics of fluid and the property of particles. In the subsequential rotor passage, in addition to these factors, particles are also affected by the stator–rotor interaction and the interference between rotors. With higher inlet temperature and larger diameter of the particle, the quantity of deposits increases and the deposition is distributed mainly on the Pressure Side (PS) and the Leading Edge (LE) of the aerofoil.

Keywords

Aero-engine turbineparticle migrationparticle depositionunsteady numerical simulation
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1291: The 25th ISABE Conference Special Issue – Part I , September 2021 , pp. 1566 - 1586
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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