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Research Papers

Heat Transfer Measurements in Rotating Blade–Shape Serpentine Coolant Passage With Ribbed Walls at High Reynolds Numbers

[+] Author and Article Information
Akhilesh Rallabandi

Turbine Heat Transfer Laboratory,
Mechanical Engineering Dept.
Texas A&M University,
College Station, TX 77843-3123

Jiang Lei

Turbine Heat Transfer Laboratory,
Mechanical Engineering Department,
Texas A&M University,
College Station, TX 77843-3123

Je-Chin Han

Turbine Heat Transfer Laboratory,
Mechanical Engineering Department,
Texas A&M University,
College Station, TX 77843-3123
e-mail: jc-han@tamu.edu

Salam Azad, Ching-Pang Lee

Siemens Energy, Inc.,
4400 Alafaya Trail,
Orlando, FL 32826

1Current address: Test R&D Engineer, Intel Corporation, 5000 West Chandler Boulevard, Chandler, AZ 85226.

2Current address: Lecturer, SKL SVMS, Xi'an Jiaotong University, Xi'an, Shaanxi 710049, China.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received January 8, 2014; final manuscript received February 18, 2014; published online March 17, 2014. Editor: Ronald Bunker.The content of this paper is copyrighted by Siemens Energy, Inc. and is licensed to ASME for publication and distribution only. Any inquiries regarding permission to use the content of this paper, in whole or in part, for any purpose must be addressed to Siemens Energy, Inc. directly.

J. Turbomach 136(9), 091004 (Mar 17, 2014) (9 pages) Paper No: TURBO-14-1002; doi: 10.1115/1.4026945 History: Received January 08, 2014; Revised February 18, 2014

Flow in the internal three-pass serpentine rib turbulated passages of an advanced high pressure rotor blade is simulated on a 1:1 scale in the laboratory. Tests to measure the effect of rotation on the Nusselt number are conducted at rotation numbers up to 0.4 and Reynolds numbers from 75,000 to 165,000. To achieve this similitude, pressurized Freon R134a vapor is utilized as the working fluid. Experimental heat transfer coefficient measurements are made using the copper-plate regional average method. Regional heat transfer coefficients are correlated with rotation numbers. An increase in heat transfer rates due to rotation is observed in radially outward passes; a reduction in heat transfer rate is observed in the radially inward pass. Strikingly, a significant deterioration in heat transfer is noticed in the “hub” region—between the radially inward second pass and the radially outward third pass. This heat transfer reduction is critical for turbine cooling designs.

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References

Figures

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Fig. 1

(a) Rotor blade cross-sectional (b) test section passages

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Fig. 2

Internal view of test section showing various regions of measurement

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Fig. 3

Internal passage view—45 deg rib arrangement

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Fig. 4

Rotating rig assembly—CAD and photographic views

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Fig. 5

Refrigerant R134a vapor working loop schematic

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Fig. 6

Variation of internal NuS/Nu0 for representative regions in the first pass (Region 3), second pass (Region 8), and third pass (Region 13). Results from region 8 are compared with Ref. [31].

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Fig. 7

Variation of internal NuS/Nu0 in regions around the first turn of the serpentine passage

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Fig. 8

Variation of internal NuS/Nu0 is regions around the second turn of the serpentine passage

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Fig. 9

Nondimensional parameter range studied

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Fig. 10

Effect of rotation: variation of internal Nu/NuS versus rotation number (Ro) for regions 3 (first pass), 8 (second pass), and 13 (third pass). Results from region 8 are compared with results from Lei et al. [33].

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Fig. 11

Effect of rotation: variation of internal Nu/NuS versus rotation number (Ro) along turn between the radially outward first pass and the radially inward second pass

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Fig. 12

Effect of rotation: variation of internal Nu/NuS versus rotation number (Ro) along the turn between the radially inward second pass and the radially outward third pass

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