Study of Particle Ingestion Through Two-Stage Gas Turbine

Ghenaiet, Adel

doi:10.1115/gt2014-25759

Cited by 8 publications

(5 citation statements)

References 13 publications

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“…It was found that the blade tip region was especially susceptible to erosion, and particles were observed to have multiple impacts on both the rotor and stator. Ghenaiet [7] studied erosion in a two-stage gas turbine using a frozen-rotor multiple reference frame model. The injected particles ranged from 1 to 150 lm, and were found to impact the trailing portion of vanes and leading edge region of rotor blades in each stage.…”

Section: Introductionmentioning

confidence: 99%

Computational Simulation of Deposition in a Cooled High-Pressure Turbine Stage With Hot Streaks

Prenter

Ameri

Bons

2017

Journal of Turbomachinery

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Ash particle deposition in a high-pressure turbine stage was numerically investigated using steady Reynolds-averaged Navier-Stokes (RANS) and unsteady Reynolds-averaged Navie-Stokes (URANS) methods. An inlet temperature profile consisting of Gaussian nonuniformities (hot streaks) was imposed on the vanes, with vane cooling simulated using a constant vane wall temperature. The steady case utilized a mixing plane at the vane–rotor interface, while a sliding mesh was used for the unsteady case. Corrected speed and mass flow were matched to an experiment involving the same geometry, so that the flow solution could be validated against measurements. Particles ranging from 1 to 65 μm were introduced into the vane domain, and tracked using an Eulerian–Lagrangian tracking model. A novel particle rebound and deposition model was employed to determine particles' stick/bounce behavior upon impact with a surface. Predicted impact and capture distributions for different diameters were compared between the steady and unsteady methods, highlighting effects from the circumferential averaging of the mixing plane. The mixing plane simulation was found to generally under predict impact and capture efficiencies compared with the unsteady calculation, as well as under predict particle temperature upon impact with the blade surface. Quantitative impact and capture efficiency trends with the Stokes number are discussed for both the vane and blade, with companion qualitative distributions for the different Stokes regimes.

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Section: Introductionmentioning

confidence: 99%

Computational Simulation of Deposition in a Cooled High-Pressure Turbine Stage With Hot Streaks

Prenter

Ameri

Bons

2017

Journal of Turbomachinery

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“…The methodology adopted here for analyzing particle ingestion in an axial compressor stage is different from that reported in the literature [9][10][11][12][13][14]. In this case, in fact, particles are not tracked through the interface between rotating and stationary domains, but the analysis is carried out by means of separate particle injections for the isolated rotor and stator cascades.…”

Section: Methodsmentioning

confidence: 99%

“…In a recent work, 117 Zagnoli et al [9] report a review of the computational studies per-118 formed in past years tracking different types of particles through 119 compressor and turbine stages. In these works, most of which deal 120 with erosion in compressors [10,11] and turbines [12][13][14], and 121 steady (mixing plane and frozen rotor) and unsteady models are 122 employed at the interface between rotating and stationary domains 123 for the rotor/stator coupling. The authors in Ref.…”

mentioning

confidence: 99%

An Innovative Method for the Evaluation of Particle Deposition Accounting for Rotor/Stator Interaction

Aldi

Morini

Pinelli

et al. 2016

Journal of Engineering for Gas Turbines and Power

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Solid particle ingestion is one of the principal degradation mechanisms in the compressor and turbine sections of gas turbines. In particular, in industrial applications, the microparticles not captured by the air filtration system can cause deposits on blading and, consequently, result in a decrease in the compressor performance. This paper presents three-dimensional numerical simulations of the microparticle ingestion (0.15–1.50 μm) in a transonic axial compressor stage, carried out by means of a commercial computational fluid dynamic code. Particles of this size can follow the main air flow with relatively little slip, while being impacted by the flow turbulence. It is of great interest to the industry to determine which zones of the compressor blades are impacted by these small particles. Particle trajectory simulations use a stochastic Lagrangian tracking method that solves the equations of motion separately from the continuous phase. A particular computational strategy is adopted in order to take into account the presence of two subsequent annular cascades (rotor and stator) in the case of particle ingestion. The proposed strategy allows the evaluation of particle deposition in an axial compressor stage, thanks to its capability of accounting for rotor/stator interaction. NASA Stage 37 is used as a case study for the numerical investigation. The compressor stage numerical model and the discrete phase model are set up and validated against the experimental and numerical data available in the literature. The blade zones affected by the particle impact and the kinematic characteristics of the impact of micrometric and submicrometric particles with the blade surface are shown. Both blade zones affected by the particle impact and deposition are analyzed. The particle deposition is established by using the quantity called sticking probability, adopted from the literature. The sticking probability links the kinematic characteristics of particle impact on the blade with fouling phenomenon. The results show that microparticles tend to follow the flow by impacting at full span with a higher impact concentration on the pressure side of rotor blade and stator vane. Both the rotor blade and stator vane suction side are only affected by the impact of smaller particles (up to 1 μm). Particular fluid dynamic phenomena, such as separation, shock waves, and tip leakage vortex, strongly influence the impact location of the particles. The kinematic analysis shows a high tendency of particle adhesion on the suction side of the rotor blade, especially for particles with a diameter equal to 0.15 μm.

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“…For example, Suzuki et al [8] numerically studied sand erosion in an axial compressor stage using an unsteady calculation with temporal grid geometry updates and found that many repeat impacts occur for both rotor and stator blades with the blade tip being the most susceptible to erosion. Ghanaiet [9] numerically studied particle ingestion in a two-stage gas turbine for particles ranging from 1 to 150 μm in size and found that the trailing edge of the pressure surface of first and second stage vanes as well as the leading edges of first and second stage blades were highly susceptible to particle impacts and subsequent erosion. Ghaneiet used a frozen rotor, multiple reference frame model to calculate the interface between stators and rotors.…”

Section: Figure 12: Damage To Turbine Blading Due To Deposition [4]mentioning

confidence: 99%

Numerical Study of Deposition in a Full Turbine Stage Using Steady and Unsteady Methods

Zagnoli

Prenter

Ameri

et al. 2015

Volume 2C: Turbomachinery

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A computational study was performed to investigate deposition phenomena in a high-pressure turbine stator and rotor stage. Steady mixing-plane and unsteady sliding mesh calculations were utilized. 3D, steady and unsteady RANS calculations were performed in conjunction with published experiments completed on identical turbine geometry in order to extract boundary conditions and to validate flow solutions. Particles were introduced into the flow domain and deposition was predicted using a Lagrangian particle tracking method with the critical viscosity model to predict deposition. For the steady method, in order to track particles from the mixing plane through the blade domain, particle positions were saved after passing through the vane domain and inserted into the blade domain using two different methods: averaged and preserved. Both methods yielded nearly identical results. For the unsteady simulation particles were tracked through a sliding mesh interface with particle position, velocity, and temperature preserved at exit of the vane domain and inlet of the blade domain. Deposition results for the steady mixing plane using both particle averaging techniques and unsteady sliding interface were compared for particles of different sizes. Large particles produced localized impact and deposit zones near the hub and tip of the pressure surface for all methods. Steady methods overpredicted impacts and deposits relative to unsteady methods by averaging out discrete unsteady vane wake motion which caused particle motion towards blade surfaces.

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Study of Particle Ingestion Through Two-Stage Gas Turbine

Cited by 8 publications

References 13 publications

Computational Simulation of Deposition in a Cooled High-Pressure Turbine Stage With Hot Streaks

Computational Simulation of Deposition in a Cooled High-Pressure Turbine Stage With Hot Streaks

An Innovative Method for the Evaluation of Particle Deposition Accounting for Rotor/Stator Interaction

Numerical Study of Deposition in a Full Turbine Stage Using Steady and Unsteady Methods

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