Swirling flow heat transfer and hydrodynamics in the model of blade cyclone cooling with inlet co-swirling flow

Wang, Dongyun; Халатов, А. А.; Shiju, E; Борисов, И. И.

doi:10.1016/j.ijheatmasstransfer.2021.121404

“…This way, more heat can be exchanged by the coolant, yielding a lower blade surface temperature. Following the early thermal investigations of cyclone cooling in swirl tubes (Glezer et al, 1996;Hedlund and Ligrani, 2000), more sophisticated experimental studies were done to analyze the internal flow structure in swirl tubes (Biegger et al, 2013) with different channel outlet geometries (Grundmann et al, 2012) and duct bends Wassermann et al (2013), Bruschewski et al (2020) and Wang et al (2021). Numerical studies were carried out to understand the swirling flow in detail Biegger et al (2015) and Seibold and Weigand (2021), but the investigated geometries are still too simplified compared to the geometry of a real turbine blade.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of the influence of film cooling hole diameter on the total cooling effectiveness for cyclone-cooled turbine blades

Bicat

¹

,

Stichling

²

,

Elfner

³

et al. 2023

J. Glob. Power Propuls. Soc.

0

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Cyclone cooling is a promising method for a more effective internal cooling of turbine rotor blades with simplified internal channels including a swirling flow to enhance internal heat transfer. Previous studies have led to the conclusion that improving the cooling performance requires an adapted film cooling design, tailored to the cyclone cooling application. In this paper, a turbine rotor blade with realistic, complex features including the cyclone cooling design is investigated experimentally using infrared thermography to capture surface temperature. The objective is to analyze the influence of increased film cooling hole diameter on a cyclone-cooled blade’s surface temperature. For this purpose, the diameter of the holes at the blade’s leading edge, which are fed by the cyclone channel, is increased. The tests are performed for different coolant mass flow rates and swirl numbers. Additionally, CFD simulations are performed to analyze the aerodynamics of the cooling air. The test results show that the surface temperature at the leading edge can be decreased by increasing the diameter of the film cooling holes, however, adversely affecting the remaining blade surface. This can be explained by a redistribution of the supplied coolant. The increase of cooling effectiveness at the leading edge is at the highest when a low swirl is generated.

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“…This way, more heat can be exchanged by the coolant, yielding a lower blade surface temperature. Following the early thermal investigations of cyclone cooling in swirl tubes [ (Glezer et al, 1996), (Hedlund and Ligrani, 2000)], more sophisticated experimental studies were done to analyze the internal flow structure in swirl tubes (Biegger et al, 2013) with different channel outlet geometries (Grundmann et al, 2012) and duct bends [ (Wassermann et al, 2013), (Bruschewski et al, 2020), (Wang et al, 2021)]. Numerical studies were carried out to understand the swirling flow in detail [ (Biegger et al, 2015), (Seibold and Weigand, 2021)], but the investigated geometries are still too simplified compared to the geometry of a real turbine blade.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of the Influence of Film Cooling Hole Diameter on the Total Cooling Effectiveness for Cyclone-Cooled Turbine Blades

Bicat¹,

Stichling²,

Elfner³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

0

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Cyclone cooling is a promising method for a more effective internal cooling of turbine rotor blades with simplified internal channels including a swirling flow to enhance internal heat transfer. Previous studies have led to the conclusion that improving the cooling performance requires an adapted film cooling design, tailored to the cyclone cooling application. In this paper, a turbine rotor blade with realistic, complex features including the cyclone cooling design is investigated experimentally using infrared thermography to capture surface temperature. The objective is to analyze the influence of increased film cooling hole diameter on a cyclone-cooled blade’s surface temperature. For this purpose, the diameter of the holes at the blade’s leading edge, which are fed by the cyclone channel, is increased. The tests are performed for different coolant mass flow rates and swirl numbers. Additionally, CFD simulations are performed to analyze the aerodynamics of the cooling air. The test results show that the surface temperature at the leading edge can be decreased by increasing the diameter of the film cooling holes, however, adversely affecting the remaining blade surface. This can be explained by a redistribution of the supplied coolant. The increase of cooling effectiveness at the leading edge is at the highest when a low swirl is generated.

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“…Swirl flow provides tangential velocity noticeable on the fluid flow downstream. Swirl flow played a vital role in producing secondary flow, which is the main factor for improving heat transfer in many thermal performance applications [1][2][3]. When the target outcome is to improve heat transfer, keeping the pressure drop at the appropriate level is still a significant challenge.…”

Section: Introductionmentioning

confidence: 99%

Thermal Performance of Four-Lobe Swirl Generator and its Transition Parts Under a Different Type of Nanofluids

Diabis

¹

,

Talib²,

Altarazi³

et al. 2022

CFDL

0

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Due to the importance of promoting the thermal performance of heat exchangers, innovating a new technique is the main goal of many researchers. In swirl flow techniques, keeping the pressure drop at the practical level still requires more and more attention. In the current paper, a numerical study is conducted to explore the impact of a novel lobe swirl generator and its transition parts on forced convective heat transfer and friction factor in a circular pipe subjected to constant heat flux.The swirl mechanism is investigated at the pitch to a diameter of P/D = 8 as the optimum design. The transition part under several parameters of variable beta (β), transition multiplier (n= 0.5) and variable helix (t = 1) have been adopted. The effect of SiO2, Al2O3, and CuO volume concentrations (1 to 5%) in water under various Reynolds numbers (Re) from 15,000 to 35,000 have been carried out. The turbulent swirling flow was modelled using the applicable shear-stress transport (SST) k-ω. The outcome demonstrated an enhancement in heat transfer value ranging from 1.35 to 1.87 with an increased pressure drop value from 1.23 to 1.67. It was also found that using SiO2/water at 5% volume concentration and Re 15000 created the highest thermal performance, with a significant factor of 1.67.

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Swirling flow heat transfer and hydrodynamics in the model of blade cyclone cooling with inlet co-swirling flow

Cited by 9 publications

References 19 publications

Experimental investigation of the influence of film cooling hole diameter on the total cooling effectiveness for cyclone-cooled turbine blades

Experimental investigation of the influence of film cooling hole diameter on the total cooling effectiveness for cyclone-cooled turbine blades

Experimental Investigation of the Influence of Film Cooling Hole Diameter on the Total Cooling Effectiveness for Cyclone-Cooled Turbine Blades

Thermal Performance of Four-Lobe Swirl Generator and its Transition Parts Under a Different Type of Nanofluids

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