Particle deposition patterns on high-pressure turbine vanes with aggressive inlet swirl

Yang, Xing; Hao, Zhiguo; Feng, Zhenping

doi:10.1016/j.cja.2021.06.005

Cited by 14 publications

(2 citation statements)

References 37 publications

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“…Different operating conditions were adopted to illustrated that the deposition distribution is mainly concentrated on the pressure side (PS) and leading edge (LE) of the vane, and the quantity of deposits strongly increases in view of higher gas temperature and larger particle sizes (Yang et al, 2020). Non-uniform inlet conditions, such as hot streaks (Prenter et al, , 2017 and inlet swirls (Yang et al, 2021a), were found to have a significant influence on the migration pattern and deposition characteristics of particles. As for rotor blade, considering the action of rotating, studies of particle deposition effect are more complicated.…”

Section: Introductionmentioning

confidence: 99%

Unsteady simulations of deposition in a rotor passage of the first-stage turbine for an aero-engine

Hao

Yang

Wang

et al. 2022

J. Glob. Power Propuls. Soc.

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Atmospheric particulate pollutants are prone to deposit in aero-engine turbines due to high-temperature and high-velocity gas flows. The resulting deposition changes the blade profile, leading to a degradation of aerodynamic performance, increase in surface roughness, and blockage of film cooling holes and internal cooling channels, which further reduces cooling performance of the blade. Therefore, the blades are easily ablated, especially for the rotating parts as they have high rotating speed. In present study, unsteady simulations on the effects of particle deposition were carried out by demonstrating the migration trajectories and deposition distributions of particles in turbine rotor passages of an aero-engine that operates at real engine conditions. The effects of rotating speed, blade tip clearance and its cavity depth on the deposition and migration of contaminant particulates were examined. Results reveal that the deposition on the blade surfaces varies with the rotating speeds and the rotor tip clearances. The deposits are mainly concentrated on the pressure side of the blade where multiple rebounds of the particles are observed under a cruise operating condition. At a larger tip clearance, more particles flow into the tip clearance due to stronger leakage flow, and the squealer tip increases the capture efficiency of the particles on the blade tip.

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Section: Introductionmentioning

confidence: 99%

Unsteady simulations of deposition in a rotor passage of the first-stage turbine for an aero-engine

Hao

Yang

Wang

et al. 2022

J. Glob. Power Propuls. Soc.

Self Cite

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“…The SW also leads to lower HPT blade loading, resulting in higher HPT blade exit Mach numbers. Xing, Yang et al [10] adopted a combustor (no HS) and NGV coupling method without considering the cooling effect. By changing the position of the swirler, it was concluded that the flow in the vane channel is strongly affected by the spatial position of the inlet SW and the direction of the SW.…”

Section: Introductionmentioning

confidence: 99%

Influence of Hot Streak and Swirl Clocking Position on Aerothermal Performance of High-Pressure Turbine

Yang,

Cai,

Kang

et al. 2023

Aerospace

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In modern civil aeroengines, the hot streak and swirl at the exit of the combustor have a significant impact on the aerothermal performance of the high-pressure turbine (HPT). Due to the different design purposes of the combustor and the turbine, hot streak (HS) and swirl (SW) have different spatial distributions at the turbine inlet. This paper conducts a transient simulation of the GE E3 first-stage HPT, considering the swirl and hot streak facing the middle of the passage and the leading edge of the nozzle guide vane, respectively, and also explores the impact of positive and negative swirl. The results show that different clocking positions and swirl directions will change the incident angle and streamline distribution of the vane, thereby affecting the migration of the hot streak, the temperature and the Nusselt number distribution on the stator surface. In positive cases, the hot streak gathers in the upper part of the passage, and in negative cases, it is in the lower part. In middle cases, high-temperature areas appear in both vanes, and the distributions are opposite. Affected by the swirl, when facing the passage center, the pressure side stagnation lines of the two vanes are also different, so the Nusselt number distribution is opposite. When facing the leading edge, only one vane appears. Due to the insensitive interference of the rotor–stator, the transient migration of the hot streak in the rotor is mainly affected by the inherent secondary flow and the temperature at the inlet of the rotor (especially the conditions facing the leading edge), while the upstream residual swirl is less affected. Unlike the middle case, in leading edge cases, the hot streak is separated and needs to be re-mixed before entering the blade passage, so the temperature change in the blade cascade is relatively gentle. Based on this, the Nusselt number distribution on the surface of the blade is similar. In order to obtain the most favorable operating conditions for the engine, the turbine efficiency is used to compare the aerothermal performance under different conditions. Ultimately, it was found that the turbine with the hot streak and positive swirl directly facing the leading edge was the most efficient.

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An experimental study on turbine vane Leading-Edge film cooling with deposition

Yang

Hao

Feng

2021

Applied Thermal Engineering

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Particle deposition patterns on high-pressure turbine vanes with aggressive inlet swirl

Cited by 14 publications

References 37 publications

Unsteady simulations of deposition in a rotor passage of the first-stage turbine for an aero-engine

Unsteady simulations of deposition in a rotor passage of the first-stage turbine for an aero-engine

Influence of Hot Streak and Swirl Clocking Position on Aerothermal Performance of High-Pressure Turbine

An experimental study on turbine vane Leading-Edge film cooling with deposition

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