Numerical investigation on the effect of rotation on impingement cooling of the gas turbine leading edge

Safi, Amin; Hamdan, Mohammad O.; Elnajjar, Emad

doi:10.1016/j.aej.2020.06.035

Cited by 22 publications

(8 citation statements)

References 18 publications

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“…The numerical study of flow field and heat transfer performance due to rotational effects on turbine blade cooling is studied using k-ω SST model (3-D) under constant heat flux supplied to leading edge and internal cooling takes place using 7 jets. The results are in accordance with the experimental results [22]. In this work, the conventional cooling of internal duct on the turbine blade surface and the effect of coolant and heat transfer around it has been analyzed with the help of simulation done on ANSYS Fluent (FVM Analysis) and performance has been observed [11], Figure 9, 10.…”

Section: Turbine Blade Cooling Through Jet Impingement -A Numerical Simulationsupporting

confidence: 80%

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Sharma¹,

Kumar²,

Singh³

et al. 2021

IJHT

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Developments in the gas turbine technology have caused widespread usage of the Turbomachines for power generation. With increase in the power demand and a drop in the availability of fuel, usage of turbines with higher efficiencies has become imperative. This is only possible with an increase in the turbine inlet temperature (TIT) of the gas. However, the higher limit of TIT is governed by the metallurgical boundary conditions set by the material used to manufacture the turbine blades. Hence, turbine blade cooling helps in drastically controlling the blade temperature of the turbine and allows a higher turbine inlet temperature. The blade could be cooled from the leading edge, from the entire surface of the blade or from the trailing edge. The various methods of blade cooling from leading edge and its comparative study were reviewed and summarized along with their advantages and disadvantages.

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Section: Turbine Blade Cooling Through Jet Impingement -A Numerical Simulationsupporting

confidence: 80%

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Sharma¹,

Kumar²,

Singh³

et al. 2021

IJHT

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“…They performed simulations that cover a range of 0–750 r/min rotating speed and revealed the mechanism of the rotational effects on the gas turbine leading edge cooling. The simulations in current research are carried out in a range of 0–4000 r/min which is similar to the rotating speed range in the research of Safi et al 30 To investigate the effects of the existence of the blade material, the “adiabatic” model is created by removing the blade material part shown in Figure 1 for comparison. The original model with the blade material part is called the ‘conjugate’ model.…”

Section: Resultsmentioning

confidence: 99%

“…Safi et al 30 conducted a numerical investigation on the rotational effects on the impingement cooling in the gas turbine leading edge. They performed simulations that cover a range of 0-750 r/min rotating speed and revealed the mechanism of the rotational effects on the gas turbine leading edge cooling.…”

Section: Resultsmentioning

confidence: 99%

Numerical investigation on conjugate heat transfer characteristics of film and vortex composite cooling under rotating conditions

Wang

Zhao

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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This paper numerically investigates the vortex and film composite cooling performance under rotating conditions. The cooling performance of the adiabatic and conjugate models is compared under the range of 0–4000 r/min. The conjugate model contains the fluid region: the cascade, the film holes, and the internal vortex cooling chamber, as well as the solid region: the blade material between the internal flow and the mainstream flow. The adiabatic model is established by removing the blade material part in the conjugate model. The dimensionless temperature θ inversely proportional to the temperature is adopted. Results show that the blade leading edge temperature doesn’t vary linearly with the rotating speed. The stagnation line of the mainstream flow on the blade leading edge moves from the pressure surface to the suction surface. The maximum θ appears at 1500 r/min when the stagnation line stays certainly on the row of film holes located on the pressure surface and is 7.86% higher than the minimum θ. The minimum θ appears at 2500 r/min when the stagnation line stays on the position between the rows of film holes. The distribution of θ is much uniform, and the value of θ is much higher in the conjugate cases than the adiabatic cases due to the heat conduction through the blade material. The highest aerodynamic parameter appears at 2000 r/min due to its relatively low blade leading edge temperature and low coolant consumption and is 41% higher than the aerodynamic parameter at 0 r/min.

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“…Hence, the SST∼γ -θ is selected in the following investigations on the VFCC. In a study by Safi et al [27], A numerical investigation was conducted to explore the rotational influences on the impingement cooling performance in the blade leading edge (BLE) of gas turbines. The simulations covered a rotating speed range of 0-750 rpm, revealing the underlying mechanism of rotational influences on the vortex and film composite cooling (VFCC) performance in the BLE of gas turbines.…”

Section: Turbulence Model Verificationmentioning

confidence: 99%

Study on Rotational Effects of Modern Turbine Blade on Coolant Injecting Nozzle Position with Film Cooling and Vortex Composite Performance

Wang,

Ng,

et al. 2023

FHMT

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The flow structure of the vortex cooling is asymmetrical compared to the traditional gas turbine leading edge cooling, such as the impingement cooling and the axial flow cooling. This asymmetrical property will affect the cooling performance in the blade leading edge, whereas such effects are not found in most of the studies on vortex cooling due to the neglect of the mainstream flow in the airfoil channel. This study involves the mainstream flow field and the rotational effects based on the profile of the GE E 3 blade to reveal the mechanism of the asymmetrical flow structure effects. The nozzle position on the characteristics of the vortex and film composite cooling in the turbine rotating blade leading edge is numerically investigated. The cool-ant injecting nozzles are set at the side of the pressure surface (PS-side-in) vs. that is set at the side of the suction surface (SS-side-in) to compare the cooling characteristics at the rotating speed range of 0-4000 rpm with fluid and thermal conjugate approach. Results show that the nozzle position presents different influences under low and higher rotational speeds. As for the mainstream flow, rotation makes the stagnation line move from the pressure surface side to the suction surface side, which changes the coolant film attachment on the blade leading edge surface. The position of nozzles, however, indicates limited influence on the coolant film flow. As for the internal channel vortex flow characteristics, the coolant injected from the nozzles forms a high-velocity region near the target wall, which brings about enhancing convective heat transfer. The flow direction of the vortex flow near the internal channel wall is opposite and aligns with the direction of Coriolis force in both the PS-side-in and SS-side-in, respectively. Therefore, the Coriolis force augments the convective heat transfer intensity of the vortex cooling in the internal channel in SS-side-in while weakening the internal heat transfer in PS-side-in. Such effects become more intense with higher rotational speed. The blade surface temperature decreases as the Coriolis force increases the internal heat transfer intensity. The SS-side-in suggests a superior composite cooling performance under the relatively higher rotating speed. The SSside-in structure is recommended in the gas turbine blade leading edge running at a higher rotating speed. KEYWORDSVortex cooling; injecting nozzle location; gas turbine; blade film cooling Abbreviation BLE Blade leading edge IVC Internal vortex cooling EFC External film cooling delta Area-averaged dimensionless temperature θ on the blade surface VFCC Vortex and film composite cooling GCI Grid Convergence Index MF Mainstream flow SST∼γ -θ SST k-ω with γ -θ transition model SST SST k-ω model SL Stagnation line

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Numerical investigation on the effect of rotation on impingement cooling of the gas turbine leading edge

Cited by 22 publications

References 18 publications

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Numerical investigation on conjugate heat transfer characteristics of film and vortex composite cooling under rotating conditions

Study on Rotational Effects of Modern Turbine Blade on Coolant Injecting Nozzle Position with Film Cooling and Vortex Composite Performance

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