A tip region film cooling study of the fan-shaped hole using PSP

Wang, Haichao; Tao, Zhi; Li, Haiwang

doi:10.1016/j.ijheatmasstransfer.2020.119378

Cited by 16 publications

(2 citation statements)

References 27 publications

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“…The effect of film cooling on the aerodynamic efficiency of turbine blades is becoming increasingly critical as the operating temperature of gas turbines is increased to improve performance [3]. CFD has now found its place among experimental and analytical methods for analyzing fluid flow, heat transfer [4][5][6][7][8][9][10], and diverse problems [11][12][13][14][15], and the use of this method for engineering analysis has become more common [16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Effects of Various Injection Holes with/without Opening Angles of Film Cooling on Blades of Gas Turbine: A CFD Approach

Hosseini

2021

Trends Sci

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The combustor exit temperature is steadily rising to improve the overall efficiency of the gas turbine. As a result, film cooling, the most important and necessary cooling technology, must be developed further to satisfy this demanding requirement. The film cooling performance on the NACA 0012 gas turbine blade is numerically evaluated in this research using 6 different injection holes with and without opening angles. The Computational Fluid Dynamics (CFD) software Ansys Fluent v16 is used to conduct 2-dimensional Reynolds-Averaged Navier-Stokes (RANS) flow and heat transfer analyses. The flow is assumed to be steady, turbulent, and incompressible. To obtain solutions, the incompressible RANS equations are solved using the finite-volume technique. The simulation results indicate that the SST k-ω turbulence model is appropriate for simulating flow characteristics and evaluating film cooling efficiency over the blade. Furthermore, the opening angle has a beneficial impact on the upper blade surface's cooling performance. The injection hole with an opening angle of 15º and a height of D (injection hole diameter) achieves the maximum value of cooling efficiency. The coolant injected from the hole provides greater cooling coverage for the entire blade in this configuration, increasing cooling effectiveness. HIGHLIGHTS The influence of various geometries of injection holes on the effectiveness of film cooling was investigated The low opening angle has a greater impact on film cooling than the other opening angles The injection hole with an opening angle eliminates the recirculation region after the coolant exits GRAPHICAL ABSTRACT

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Section: Introductionmentioning

confidence: 99%

Effects of Various Injection Holes with/without Opening Angles of Film Cooling on Blades of Gas Turbine: A CFD Approach

Hosseini

2021

Trends Sci

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“…The results showed that the film effectiveness is associated both with the tip clearance and coolant mass flow rates. Wang et al [3] compared the effect of cylindrical and fan-shaped tip bleed holes on the film cooling performance. The experimental results indicated that the cylindrical hole film cooling performance is better than that of the fan-shaped hole, but the fan-shaped hole film coverage area expanded as the blowing ratio increased while that of the cylindrical hole decreased gradually.…”

Section: Introductionmentioning

confidence: 99%

Vortical structures and heat transfer augmentation of a cooling channel in a gas turbine blade with various arrangements of tip bleed holes

Zhao

Luo

Qiu

et al. 2020

Numerical Heat Transfer, Part A: Applications

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This study investigates the internal cooling processes affected by the tip bleed holes in gas turbine blades. Double bleed holes are fixed at the center of the blade tip near the pressure side and suction side, respectively. Five different arrangements of the holes along the center line of the tip are studied. The purely double holes are set as the Baseline. The purpose of the present study is to provide a new perspective of the tip film cooling to understand the internal flow processes, vorticity evolution and the mechanism of the heat transfer augmentation. A topological analysis and the boundary layer analysis methods are introduced to better understand the tip heat transfer. The total extraction area and volume is kept at the same level for all the studied cases. The results show that the Dean vortices and the near-wall vortices induced by the secondary flow contribute to the high heat transfer coefficient on the tip surface. The mixing effect of the Dean vortices and the hole extraction helps to enhance heat transfer upstream of the tip. Different arrangement of the bleed holes can affect the internal flow processes and heat transfer performance. The suction effect of the center-line bleed hole can accelerate the near-hole flow and reduce the thickness of the boundary layer. The center-line hole fitted at the middle of the tip affects significantly the rear side of the hole. Thus, the holes aligned in the middle of the tip provide the highest heat transfer and thermal performance. The thermal performance is enhanced by up to 4.7% compared with the Baseline.

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Cooling Performance of the Endwall Vertical Hole Considering the Interaction between Cooling Jet and Leading-Edge Horseshoe Vortex

Chen

Yuan

2022

J. Therm. Sci.

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A tip region film cooling study of the fan-shaped hole using PSP

Cited by 16 publications

References 27 publications

Effects of Various Injection Holes with/without Opening Angles of Film Cooling on Blades of Gas Turbine: A CFD Approach

Effects of Various Injection Holes with/without Opening Angles of Film Cooling on Blades of Gas Turbine: A CFD Approach

Vortical structures and heat transfer augmentation of a cooling channel in a gas turbine blade with various arrangements of tip bleed holes

Cooling Performance of the Endwall Vertical Hole Considering the Interaction between Cooling Jet and Leading-Edge Horseshoe Vortex

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