Heat Transfer in a Rotating, Blade-Shaped Serpentine Cooling Passage With Discrete Ribbed Walls at High Reynolds Numbers

Wright, Lesley M.; Yang, Shang-Feng; Wu, Hao-Wei; Han, Je-Chin; Lee, Ching-Pang; Azad, Salam; Um, Jae Yeon

doi:10.1115/1.4045243

Cited by 9 publications

(2 citation statements)

References 28 publications

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“…Han 6,7,8 did a lot of research about internal ribbed turbulator in gas turbine blades. The investigations include the effects of rib spacing, angle, arrangement, shape, rotating and other parameters.…”

Section: Introductionmentioning

confidence: 99%

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Numerical study on the effect of different internal angled ribs on the external film cooling performance

Cheng

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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For the blades of gas turbine, the traditional internal ribs have a great impact on the film cooling heat transfer of blade external surface. In this study, SST k-ω turbulence coupled with transition model is adopted to study the effects of angled ribbed passages on external flow and heat transfer characteristics. The detailed flow characteristics were analyzed for two vertically placed flat-plate channels with the blowing ratios of 0.5∼2. The computational model includes a single film hole ( D = 20 mm) with a jet angle of 35°. Four different rib orientations in the secondary flow channels are designed. They are no rib, oblique rib 1 (30° angle from the horizontal line), oblique rib 2 (symmetrical to oblique rib 1), and straight rib. Compared with ribless channel, the average adiabatic film cooling effectiveness of straight rib, Oblique rib 1, Oblique rib 2 are 2.3, 2.2, and 1.9 times higher at different Reynolds numbers, respectively. Taking the film hole as the origin, Oblique rib 2 can greatly improve the overall cooling effectiveness. Oblique rib 1 can improve the cooling effectiveness of the farther downstream wall surface. The comparison of film cooling efficiency, coolant coverage area, flow behavior inside the film hole and that in the downstream, heat transfer and transition behavior for different channels are also analyzed separately. Through the investigations, it helps to understand the effects of internal rib angle on the flow, friction factor and heat transfer outside the film holes.

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Section: Introductionmentioning

confidence: 99%

“…It had the similar trend for the pressure gradient. Samson and Sarkar 8 investigated the inception of separation from the same semi-circular airfoil model in a low-speed wind tunnel. The turbulence intensities and velocity are tested with PIV and Laser-Doppler Anemometry (LDA).…”

Section: Introductionmentioning

confidence: 99%

Numerical study on the effect of different internal angled ribs on the external film cooling performance

Cheng

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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Heat Transfer in a Rotating, Two-Pass, Variable Aspect Ratio Cooling Channel With Profiled V-Shaped Ribs

Chen

Sahin

Wright

et al. 2021

Journal of Turbomachinery

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The thermal performance of two V-type rib configurations is measured in a rotating, two-pass cooling channel. The coolant travels radially outward in the rectangular first pass (AR = 4:1), and travels radially inward in the second pass (AR = 2:1). Both the passages are oriented 90° to the direction of rotation. The LS and TS of the channel are roughened with V-type ribs. The first V-shaped configuration has a narrow gap at the apex of the V. The configuration is modified by off-setting one leg of the V to create a staggered discrete, V-shaped configuration. The ribs are oriented 45° relative to the streamwise coolant direction. The heat transfer enhancement and frictional losses are measured with varying Reynolds and rotation numbers. The Reynolds number varies from 10,000 to 45,000 in the AR = 4:1 first pass; this corresponds to 16,000 to 73,500 in the AR = 2:1 second pass. The maximum rotation numbers are 0.39 and 0.16 in the first and second passes, respectively. The heat transfer enhancement on both the leading and trailing surfaces of the first pass of the 45° V-shaped channel is slightly reduced with rotation. In the second pass, the heat transfer increases on the leading surface while it decreases on the trailing surface. The 45° staggered, discrete V-shaped ribs provide increased heat transfer and thermal performance compared to the traditional V-shaped and standard, 45° angled rib turbulators.

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Heat Transfer and Pressure Loss in a Two-Pass, Rectangular Channel Featuring a Reduced Cross-Sectional Area After the 180-Deg Tip Turn With Different Turning Vane Configurations

Alsaleem

Wright

Han

2021

Journal of Turbomachinery

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Serpentine, multi-pass cooling passages, are used in cooling advanced gas turbine blades. In open literature, most internal cooling studies use a fixed cross-sectional area for multi-pass channels. Studies that use varying aspect ratio channels, along with a guide vane to direct the flow with turning, are scarce. Therefore, this study investigates the effect of using different guide vane designs on both detailed heat transfer distribution and pressure loss in a multi-pass channel with an aspect ratio of (4:1) in the entry passage and (2:1) in the second passage downstream of the vane (s). The first vane configuration is one solid-vane with a semi-circular cross-section connecting the two flow passages. The second configuration has three broken-vanes with a quarter-circular cross-section; two broken vanes are located downstream in the first passage, and one broken vane is upstream in the second passage. Detailed heat transfer distributions were obtained on all surfaces within the flow passages by using a transient liquid crystal method. Results show that including the semi-circular vane in the turning region enhanced the overall heat transfer by around 29% with a reduction in pressure loss by around 20%. Moreover, results show the quarter-circular vane design provides higher overall averaged heat transfer enhancement than the semi-circular vane design by around 9% with penalty of higher pressure drop by 6%, which yields higher thermal performance by 7%, over a Reynolds number range from 15,000 to 45,000.

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Heat Transfer in a Rotating, Blade-Shaped Serpentine Cooling Passage With Discrete Ribbed Walls at High Reynolds Numbers

Cited by 9 publications

References 28 publications

Numerical study on the effect of different internal angled ribs on the external film cooling performance

Numerical study on the effect of different internal angled ribs on the external film cooling performance

Heat Transfer in a Rotating, Two-Pass, Variable Aspect Ratio Cooling Channel With Profiled V-Shaped Ribs

Heat Transfer and Pressure Loss in a Two-Pass, Rectangular Channel Featuring a Reduced Cross-Sectional Area After the 180-Deg Tip Turn With Different Turning Vane Configurations

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