Comparison between impingement/effusion and double swirl/effusion cooling performance under different effusion hole diameters

Zhou, Jifu; Wang, Xinjun; Li, Jun; Hou, Weitao

doi:10.1016/j.ijheatmasstransfer.2019.07.055

Cited by 21 publications

(3 citation statements)

References 36 publications

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“…Wassermann et al 10 conducted an experiment to investigate the impacts of different vortex chamber outlet shapes on the thermal transfer intensity. Based on the double-swirl cooling structure, Zhou et al 11 explored the thermal exchange and flow operations under different film hole angles and diameters. The heat transfer capacity of three groups for film cooling hole rows were compared.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on vortex cooling flow and heat transfer characteristics for gas turbine blade with variable coolant chamber cross-sectional shapes

Li,

Gao,

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this paper, according to the actual size of gas turbine blade interior space, eight vortex cooling models with different cross-sectional shapes of coolant chambers are established. Rectangular, Circle, Trapezoidal up, Trapezoidal down, Ellipse up, Ellipse down, Sine up and Sine down are the eight coolant chamber shapes. Functions of variable coolant chamber structures on vortex cooling flow and heat exchange characteristics are numerically analyzed by verifying the Standard k- ω turbulence model and conducting grid independence analysis. Research results show that the heat exchange ability of Sine up coolant chamber is the best compared with the other coolant chambers. The cool air enters the vortex chamber at a faster speed and impacts on the target surface to form a high-pressure area and a low-temperature swirl. The more the cool air moves downstream, the greater the turbulent kinetic energy becomes, which is more conducive to the heat transfer. Therefore, Sine up coolant chambers have the highest thermal performance factor. Due to the low drag coefficient and high target surface average Nusselt number of Ellipse up, its thermal exchange performance is second only to that of Sine up. Circle coolant chamber will not bring favorable factors to engineering application because of the slowest flow speed and the worst heat exchange capacity. For Trapezoidal up and Trapezoidal down, the flow velocity, pressure distribution, turbulent kinetic energy intensity and heat transfer uniformity are almost the same as Rectangle coolant chamber. The models of Ellipse down and Sine down coolant chambers exhibit less turbulent kinetic energy strength to heat transfer and higher temperature in the vortex chamber, and it is not suggested for cooling system optimal design.

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Section: Introductionmentioning

confidence: 99%

Numerical investigation on vortex cooling flow and heat transfer characteristics for gas turbine blade with variable coolant chamber cross-sectional shapes

Li,

Gao,

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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show abstract

“…Cho et al [9][10][11] researched the arrangements of impingement with effusion cooling holes and the local heat and mass transfer characteristics on the target surface, the staggered hole arrangement had better cooling performance because of generate vortex. Zhou et al 12 analyzed the flow and heat transfer characteristics of the impingement cooling and double swirl cooling with different film cooling hole diameters. Li et al 13 experimental measured the hole diameters/length ratio on the impingement and effusion cooling system.…”

Section: Introductionmentioning

confidence: 99%

Investigation on flow field and heat transfer characteristics of film cooling with different swirling directions for coolant flow

Zhang

Zheng

Yue

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this paper, a hexagonal prism inlet chamber is used to form a swirling flow for the film cooling, and three kinds of compound angle of film hole ( γ = 10°, 20°, 30°) with clockwise swirling or counterclockwise swirling are used for numerical simulation studies. The influence of different compound angles of film hole and the swirling directions for the film cooling effectiveness are obtained. The results show that the film cooling effectiveness and spanwise cooling coverage range of the clockwise swirling or counterclockwise swirling flow both are low when the compound angle of film hole is 10°. With the increasing compound angle of film hole, the kidney shaped vortex of film hole exit gradually weakens until it disappears, which reduces the entrainment effect by the coolant jet. So that the spanwise coverage range of two swirling modes is obviously improved. When the compound angle of film hole is 30° compared to 10°, the average spanwise film cooling effectiveness of clockwise swirling and counterclockwise swirling are increased by about 133.75 and 212.6%, respectively. The average spanwise film cooling effectiveness on the downstream of film hole for counterclockwise swirling is increased by about 140% compared with clockwise swirling.

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“…Results showed that the heat transfer increased with the increase of Reynolds number of the impinging jet. Zhou et al [37] introduced a study of the influences of the film hole diameter on heat transfer and flow characteristics for impingement and swirl cooling. Results indicated that by using a double swirl tube, there was about a 20% to 33% increase in overall Nusselt number.…”

Section: Introductionmentioning

confidence: 99%

Optimization of A Swirl with Impingement Compound Cooling Unit for A Gas Turbine Blade Leading Edge

et al. 2020

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In this article, a compound unit of swirl and impingement cooling techniques is designed to study the performance of flow and heat transfer using multi-conical nozzles in a leading-edge of a gas turbine blade. Reynolds Averaged Navier-Stokes equations and the Shear Stress Transport model are numerically solved under different nozzle Reynolds numbers and temperature ratios. Results indicated that the compound cooling unit could achieve a 99.7% increase in heat transfer enhancement by increasing the nozzle Reynolds number from 10,000 to 25,000 at a constant temperature ratio. Also, there is an 11% increase in the overall Nusselt number when the temperature ratio increases from 0.65 to 0.95 at identical nozzle Reynolds number. At 10,000 and 15,000 of nozzle Reynolds numbers, the compound cooling unit achieves 47.9% and 39.8% increases and 63.5% and 66.3% increases in the overall Nusselt number comparing with the available experimental swirl and impingement models, respectively. A correlation for the overall Nusselt number is derived as a function of nozzle Reynolds number and temperature ratio to optimize the results. The current study concluded that the extremely high zones and uniform distribution of heat transfer are perfectly achieved with regard to the characteristics of heat transfer of the compound cooling unit.

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Comparison between impingement/effusion and double swirl/effusion cooling performance under different effusion hole diameters

Cited by 21 publications

References 36 publications

Numerical investigation on vortex cooling flow and heat transfer characteristics for gas turbine blade with variable coolant chamber cross-sectional shapes

Numerical investigation on vortex cooling flow and heat transfer characteristics for gas turbine blade with variable coolant chamber cross-sectional shapes

Investigation on flow field and heat transfer characteristics of film cooling with different swirling directions for coolant flow

Optimization of A Swirl with Impingement Compound Cooling Unit for A Gas Turbine Blade Leading Edge

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