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Research Papers

Effects of Target Channel Shapes on Double Swirl Cooling Performance at Gas Turbine Blade Leading Edge

[+] Author and Article Information
Junfei Zhou, Jun Li, Weitao Hou

Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China

Xinjun Wang

Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
e-mail: xjwang@xjtu.edu.cn

1Corresponding author.

Manuscript received July 5, 2018; final manuscript received December 14, 2018; published online January 11, 2019. Assoc. Editor: Riccardo Da Soghe.

J. Eng. Gas Turbines Power 141(7), 071004 (Jan 11, 2019) (15 pages) Paper No: GTP-18-1449; doi: 10.1115/1.4042311 History: Received July 05, 2018; Revised December 14, 2018

In order to further study the effects of the target channel shape on the cooling performance of the double swirl cooling (DSC), five double swirl channels formed by two overlapping elliptic cylinders with different length ratio between the vertical semi-axis and the horizontal semi-axis are applied. Numerical studies are carried out under three Reynolds numbers. The flow characteristics and heat transfer performance of five DSC cases are compared with the benchmark impingement cooling case. The flow losses, cross-flow development, generated vortices, and velocity distributions inside target channels are illustrated, analyzed, and compared. The spanwise averaged Nusselt number, Nusselt number distributions, and thermal performance are discussed and compared. Results indicate that the largest length ratio between the vertical semi-axis and the horizontal semi-axis of the target channel yields the lowest flow loss, largest overall averaged Nusselt number, and best thermal performance. With the decrease in the length ratio, the heat transfer distribution on the target surface becomes more uniform. The maximum enhancement of overall averaged Nusselt number and thermal performance in DSC is about 30% and 33%, respectively.

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Figures

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Fig. 1

Schematic views of impingement cooling and DSC structures

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Fig. 2

Schematic views of the template structure [26]: (a) front view of the template structure and (b) side view of the template structure

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Fig. 3

Schematic views of investigated cooling structures: (a) target channel contours, (b) 3D view of DSC3, and (c) details of target channels in six cases

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Fig. 4

Schematic views of the meshing in the benchmark impingement cooling case

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Fig. 5

Grid independence study of six numerical models: (a) grid independence analysis and (b) GCI error analysis

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Fig. 6

Comparison between numerical and experimental results with full domain: (a) spanwise averaged NuD and (b) NuD contour

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Fig. 7

Comparison of numerical results between half domain and full domain of the template structure: (a) spanwise averaged NuD and (b) NuD contour

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Fig. 8

Comparison of flow characteristics predicted by S-A and SST kω turbulence models with half domain and full domain: (a) mass velocity ratio of cross flow to jet flow and (b) average eddy viscosity of cross sections

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Fig. 9

Comparison of predicted cooling air streamline and eddy viscosity contour between S-A and SST kω turbulence models with half domain and full domain: (a) S-A half domain, (b) S-A full domain, (c) SST kω half domain, and (d) SST kω full domain

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Fig. 10

Comparison of normalized NuD distributions on the target surface centerline between numerical resutls and experimental results [34] in impingement cooling

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Fig. 11

Comparison of normalized NuD contours between numerical and experimental results [34] in impingement cooling: (a) target plate, (b) side wall, and (c) impingement plate

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Fig. 12

Comparison between numerical results and experimental results [35] in swirl cooling: (a) simplified numerical model based on the experimental model in Ref. [35], (b) spanwise averaged NuD, and (c) NuD contours on the target surface

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Fig. 13

Schematic view of streamlines and tangential velocity contours at five yz cross sections in six cases under ReD = 15,000

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Fig. 14

Dimensionless tangential velocity vectors colored by static pressure at the symmetry plane of the double swirl channel under ReD = 15,000: (a) benchmark impingement cooling case and (b) five DSC cases

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Fig. 15

Tangential velocity contours at the symmetry plane in all cases under ReD = 15,000

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Fig. 16

Mass velocity ratio of cross flow to jet flow in six cases under three ReD

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Fig. 17

Comparison of the spanwise averaged Nusselt number in the effective cooling region under different ReD

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Fig. 18

Comparison of the spanwise averaged Nusselt number in the effective cooling region among different cases: (a)ReD = 10,000, (b) ReD = 15,000, and (c) ReD = 20,000

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Fig. 19

NuD contours from the bottom view of the target channel in six cases under ReD = 15,000

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Fig. 20

NuD contours from the top view of the target channel in six cases under ReD = 15,000

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