Effects of simulated swirl purge flow and mid-passage gap leakage on turbine blade platform cooling and suction surface phantom cooling performance

Zhang, Kaiyuan; Li, Jun; Li, Zhigang; Song, Liming

doi:10.1016/j.ijheatmasstransfer.2018.09.111

Cited by 22 publications

(5 citation statements)

References 22 publications

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“…Zhang et al [55] presented a numerical study on the effects of swirl ratio, density ratio and blowing ratio on the cooling capability of an upstream slot and a mid-passage gap. RANS modelling, along with the k − ω SST turbulence model, was adopted to assess the parameter sensitivity when operating at different swirl ratio values.…”

Section: Blade Cascade Research With Simulated Rotation Effectsmentioning

confidence: 99%

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The Aero-Thermal Performance of Purge Flow and Discrete Holes Film Cooling of Rotor Blade Platform in Modern High Pressure Gas Turbines: A Review

Barigozzi

Abdeh

Rouina

et al. 2022

IJTPP

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Design of cooling systems for rotor platforms is critical due to the complex flow field and heat transfer phenomena related to the secondary flow structures originating at the blade leading edge. Horseshoe vortex and passage vortex are the fluid-dynamic features that largely influence the aerodynamic behaviour and the thermal protection level of the platform. The driving parameter is the coolant to mainstream momentum flux ratio, but several issues have to be considered in the design process of cooling technologies. As well acknowledged, an in-depth understanding of losses and heat transfer phenomena are deemed necessary to design effective cooling systems. In the present review, measurements and predictions on the behaviour of the HPT rotor cooled platform, obtained during the last two decades by several research groups, are gathered, described and analysed in terms of aerodynamic losses and heat transfer performance, and are compared with one another with respect to the effectiveness level that is ensured.

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Section: Blade Cascade Research With Simulated Rotation Effectsmentioning

confidence: 99%

“…Ref. [55] observed that phantom cooling may have noticeable effects for SS cooling but also highlighted that the effectiveness could be significantly reduced for higher relative motion conditions. In fact, complex interaction occurs between primary and secondary sources of cooling, as also shown in [59].…”

Section: Phantom Coolingmentioning

confidence: 99%

The Aero-Thermal Performance of Purge Flow and Discrete Holes Film Cooling of Rotor Blade Platform in Modern High Pressure Gas Turbines: A Review

Barigozzi

Abdeh

Rouina

et al. 2022

IJTPP

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“…When calculating the endwall cooling characteristics, surfaces are set to be adiabatic and nonslip. Because the temperature difference between hot mainstream and coolant is small in this study, the heat transfer of the endwall can be approximately calculated using two simulations 24 : an adiabatic wall boundary condition case to determine adiabatic wall temperature (T aw ), and an isothermal endwall boundary condition case to determine endwall heat flux (q w ).…”

Section: Boundary Conditionsmentioning

confidence: 99%

“…Figure 14 shows the phantom cooling effectiveness contours on surface 1 which covers 20% of the blade suction side surface. From our previous study, 24 it was found that the slashface leakage is brought by the passage vortex onto blade suction side surface to have some phantom cooling effect, and the back part of the suction side surface is the major affected area as marked out by dashed line. The fore part phantom cooling is caused by unchanged slot injection instead of slashface leakage, and is therefore not discussed in this study.…”

Section: Blade Suction Side Surface Phantom Coolingmentioning

confidence: 99%

“…The coolant from endwall may still have some cooling effect on turbine airfoil even after mixing with hot mainstream, and it is one of the major types of phantom cooling in the turbine. 24 Roback et al 25 documented the phantom cooling effect of hot and cold streak on turbine airfoil. Zhang et al 26 used the PSP technique to experimentally analyze the phantom cooling effectiveness on vane surface under different film cooling hole diameters.…”

Section: Introductionmentioning

confidence: 99%

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Influence of slashface leakage coupled with quasi-labyrinth seal technique on gas turbine endwall aerothermal performance and blade suction side surface phantom cooling

Zhang

2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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Quasi-labyrinth seal technique was innovatively adopted to control the slashface flow, and the effect of slashface leakage on endwall aerothermal performance and blade suction side surface phantom cooling was numerically investigated. Simulations of five different labyrinth seal lengths ( Ls) and three coolant momentum flux ratios ( I) were conducted by computationally solving the Reynolds-averaged Navier–Stokes equations coupled with the shear stress transport k-ω turbulence model. The results show that the slashface coolant can be accelerated and conveyed downstream inside the slashface carried by the ingested mainstream and passage vortex. By setting up the quasi-labyrinth seal composed of a series of aperture cavities along the slashface, the coolant downstream transportation can be largely weakened, and the labyrinth seal with various lengths all have the potential to move the endwall coolant coverage toward upstream. When I = 0.48, the coolant downstream migration is severest and it has the best coverage on the endwall with seal. The laterally averaged cooling effectiveness is elevated for the fore part endwall but decreased for the back part endwall after sealing, and the highest cooling effectiveness is increased by 5% for 0.6 Ls seal. The 0.6–1.0 Ls seal has the approximate effect and is better than 0.4 Ls seal, and 0.6 Ls seal has the best outcome considering the countering effects of structural strength and endwall cooling performance. For 0.6 Ls sealed case, the high heat transfer level caused by coolant attachment is enhanced by 3.5% when I = 0.48 but decreased by 3.3% and 4.4% when I = 0.96 and 1.42 compared with baseline case. The low heat transfer caused by horseshoe vortex separation is enhanced when I = 1.42 for the sealed case. The quasi-labyrinth seal mainly weakens the back part suction side phantom cooling performance, and the well phantom cooling region moves upstream with the increase of I. The averaged phantom cooling effectiveness is decreased by 0.56%, 0.3%, and 1.44% when I = 0.48, 0.96, and 1.42 for the sealed cases. The results provide the gas turbine designers a better insight into improved slashface leakage control as well as its detailed surface cooling effects.

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Thermal Insulation Effect of TBCs on Turbine Blades

Zhou

Yang

Zhu

2022

Thermal Barrier Coatings: Failure Theory and Evaluation Technology

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Effects of simulated swirl purge flow and mid-passage gap leakage on turbine blade platform cooling and suction surface phantom cooling performance

Cited by 22 publications

References 22 publications

The Aero-Thermal Performance of Purge Flow and Discrete Holes Film Cooling of Rotor Blade Platform in Modern High Pressure Gas Turbines: A Review

The Aero-Thermal Performance of Purge Flow and Discrete Holes Film Cooling of Rotor Blade Platform in Modern High Pressure Gas Turbines: A Review

Influence of slashface leakage coupled with quasi-labyrinth seal technique on gas turbine endwall aerothermal performance and blade suction side surface phantom cooling

Thermal Insulation Effect of TBCs on Turbine Blades

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