Characterization of component interactions in two-stage axial turbine

Ghenaiet, Adel; Touil, Kaddour

doi:10.1016/j.cja.2016.06.007

Cited by 10 publications

(4 citation statements)

References 16 publications

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“…The first stage was not affected by the second stage, but the second stage was strongly affected by the first stage. It was found that the upstream flow caused distortion in the downstream flow along the circumferential direction, and the flow interacts with the secondary flow and tip leakage flow of the blade [14]. Therefore, it is necessary to accurately understand the Energies 2018, 11, 2654 3 of 15 effect of the first stage flow on the second-stage and predict the thermal and flow characteristics within the passage and the heat transfer distribution of the blade surface.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

Choi

Ryu

2018

Energies

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Combined cycle power plants (CCPPs) are becoming more important as the global demand for electrical power increases. The power and efficiency of CCPPs are directly affected by the performance and thermal efficiency of the gas turbines. This study is the first unsteady numerical study that comprehensively considers axial gap (AG) in the first-stage stator and first-stage rotor (R1) and hot streaks in the combustor outlet throughout an entire two-stage turbine, as these factors affect the aerodynamic performance of the turbine. To resolve the three-dimensional unsteady-state compressible flow, an unsteady Reynolds-averaged Navier-Stokes (RANS) equation was used to calculate a k − ω SST γ turbulence model. The AG distance d was set as 80% (case 1) and 120% (case 3) for the design value case 2 (13 mm or d/Cs 1 = 0.307) in a GE-E 3 gas turbine model. Changes in the AG affect the overall flow field characteristics and efficiency. If AG decreases, the time-averaged maximum temperature and pressure of R1 exhibit differences of approximately 3 K and 400 Pa, respectively. In addition, the low-temperature zone around the hub and tip regions of R1 and second-stage rotor (R2) on the suction side becomes smaller owing to a secondary flow and the area-averaged surface temperature increases. The area-averaged heat flux of the blade surface increases by a maximum of 10.6% at the second-stage stator and 2.8% at R2 as the AG decreases. The total-to-total efficiencies of the overall turbine increase by 0.306% and 0.295% when the AG decreases.

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Section: Introductionmentioning

confidence: 99%

Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

Choi

Ryu

2018

Energies

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“…Two harmonics are predicted showing the blade passing frequency (BPF = 8171 Hz) where the second harmonic represents 23% of the energy contained in the BPF. Note that the number of harmonics is sensitive to the probe location [45] (e.g., near the midspan or the endwalls), the probed quantity [46] (e.g., static pressure, axial velocity, turbulent kinetic energy, etc.). However, the adopted URANS model (SST γ -Re θ ) showed that it is capable to predict the same number of harmonics compared to Large Eddy Simulation (LES) as reported in [47] .…”

Section: Numerical Setupmentioning

confidence: 99%

Heat transfer characteristics of a high-pressure turbine under combined distorted hot-streak and residual swirl: an unsteady computational study

Mansouri

Jefferson-Loveday

2022

International Journal of Heat and Mass Transfer

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“…When it comes to managing power the partial admission turbine plays an important role as it strengthens the unsteady flow. Several other theories were used throughout the ages and have been improving and developing the present day turbines with higher efficiency [2,4,6,9].…”

Section: Literature Review Theoretical Analysis On Axial Flow Turbinementioning

confidence: 99%

The Numerical Simulation and Evaluation of Aircraft Engine Axial Flow Turbine using Numerical Techniques

al.¹

2019

IJMPERD

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This research aims to improve the efficiency of an axial flow turbine by improving the boundary conditions. In the baseline paper, Sherwood number, Nusselts number for a given flow were determined. The pressure ratio was not considered in the paper. Research has been done to improve the values by considering the pressure difference which was neglected in the base line paper. Axial flow turbines expand the flow passing through it. Losses like tip losses, efficiency losses and loss on blades due to heat are high and needs to be looked after. A comprehensive literature study was carried out for the better understanding of axial flow turbines, recent developments and to analyze the control of loses.

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Characterization of component interactions in two-stage axial turbine

Cited by 10 publications

References 16 publications

Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

Heat transfer characteristics of a high-pressure turbine under combined distorted hot-streak and residual swirl: an unsteady computational study

The Numerical Simulation and Evaluation of Aircraft Engine Axial Flow Turbine using Numerical Techniques

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