Unsteady simulations of migration and deposition of fly-ash particles in the first-stage turbine of an aero-engine. (12th September 2021)

• Record Type: Journal Article
• Authors: Hao, Z.; Yang, X.; Feng, Z.
• Is Part Of: Aeronautical journal. Volume 125:Number 1291(2021)
• Page Start: 1566
• Page End: 1586
• Publication Date: 2021-09-12
• Subjects: Aero-engine turbine -- particle migration -- particle deposition -- unsteady numerical simulation; Aeronautics -- Periodicals; 629.1305
• DOI: 10.1017/aer.2021.27
• Languages: English
• ISSNs: 0001-9240

Abstract

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.