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Research Papers

Effects of Inlet Swirl on Pressure Side Film Cooling of Neighboring Vane Surface

[+] Author and Article Information
Yang Zhang

Key Laboratory for Thermal Science and Power Engineering of Ministry of Education,
Department of Energy and Power Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: yangzhang2014@mail.tsinghua.edu.cn

Yifei Li

Key Laboratory for Thermal Science and Power Engineering of Ministry of Education,
Department of Energy and Power Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: liyifei14@mails.tsinghua.edu.cn

Xiutao Bian

Key Laboratory for Thermal Science and Power Engineering of Ministry of Education,
Department of Energy and Power Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: bxt15@mails.tsinghua.edu.cn

Xin Yuan

Key Laboratory for Thermal Science and Power Engineering of Ministry of Education,
Department of Energy and Power Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: yuanxin@mail.tsinghua.edu.cn

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the Journal of Thermal Science and Engineering Applications. Manuscript received October 17, 2017; final manuscript received February 18, 2019; published online May 13, 2019. Assoc. Editor: Ting Wang.

J. Thermal Sci. Eng. Appl 11(6), 061008 (May 13, 2019) (12 pages) Paper No: TSEA-17-1396; doi: 10.1115/1.4043260 History: Received October 17, 2017; Accepted February 18, 2019

The lean combustion chamber of low NOx emission engines has a short distance between combustion outlet and nozzle guide vanes (NGVs), with strong swirlers located upstream of the turbine inlet to from steady circulation in the combustion region. Although the lean combustion design benefits emission control, it complicates the turbine’s aerodynamics and heat transfer. The strong swirling flow will influence the near-wall flow field where film cooling acts. This research investigates the influence of inlet swirl on the film cooling of cascades. The test cascades are a 1.95 scale model based on the GE-E3 profile, with an inlet Mach number of 0.1 and Reynolds number of 1.48 × 105. Film cooling effectiveness is measured with pressure-sensitive paint (PSP) technology, with nitrogen simulating coolant at a density ratio of near to 1.0. Two neighboring passages are investigated simultaneously, so that pressure and suction side the film cooling effectiveness can be compared. The inlet swirl is produced by a swirler placed upstream, near the inlet, with five positions along the pitchwise direction. These are as follows: blade 1 aligned, passage 1–2 aligned, blade 2 aligned, passage 2–3 aligned and blade 3 aligned. According to the experimental results, the near-hub region is strongly influenced by inlet swirl, where the averaged film cooling effectiveness can differ by up to 12% between the neighboring blades. At the spanwise location Z/Span = 0.7, when the inlet swirl is moved from blade 1 aligned (position 5) to blade 2 aligned (position 3), the film cooling effectiveness in a small area near the endwall can change by up to 100%.

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Figures

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Fig. 1

Calibration curve for PSP

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Fig. 2

Schematic of cascade test rig

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Fig. 3

Test rig with excitation lights and the CCD camera

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Fig. 4

Geometric parameters of film cooling holes and secondary air supply system

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Fig. 5

Geometric parameters of coolant plenums

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Fig. 6

Five-hole probe and its two-dimensional displacement worktable

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Fig. 7

Nondimensional pressure coefficient distributions on airfoil

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Fig. 8

Spatially resolved map of nondimensional total pressure loss without film cooling

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Fig. 9

Structure in detail of double-passage test section and swirler

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Fig. 10

Selected region for film cooling effectiveness distribution measurement (Three blades with two passages, X/Cax = nondimensional X position based on the axial length, Z/Zp = nondimensional blade spanwise position Z based on the blade span)

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Fig. 11

Film cooling effectiveness distribution with different swirler positions (M = 0.5, the distribution is shown on blade 1 and blade 2)

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Fig. 12

Near-hub flow structures and the low blowing ratio region

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Fig. 13

Film cooling effectiveness distribution with different swirler positions (M = 1.0, the distribution is shown on blade 1 in left subplot and blade 2 in right subplot)

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Fig. 14

Spanwise-averaged film cooling effectiveness in passage 1 with different swirler positions (M = 0.5, left and M = 1.0, right)

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Fig. 15

Spanwise-averaged film cooling effectiveness in passage 2 with different swirler positions (M = 0.5, left and M = 1.0, right)

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Fig. 16

Film cooling effectiveness distribution at the same axial position (line 1 and line 3) in different passages with swirler at position 3 (M = 0.5, left and M = 1.0, right)

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Fig. 17

Film cooling effectiveness distribution at the same axial position (line 1 and line 3) in different passages with swirler at position 5 (M = 0.5, left and M = 1.0, right)

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Fig. 18

Film cooling effectiveness distribution at the same axial position (line 2 and line 4) in different passages with swirler at position 5 (M = 0.5, left and M = 1.0, right)

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