Research Papers

Aerothermal Investigations on Mixing Flow Field of Film Cooling With Swirling Coolant Flow

[+] Author and Article Information
Kenichiro Takeishi

e-mail: takeishi@mech.eng.osaka-u.ac.jp

Masaharu Komiyama

e-mail: komiyama@mech.eng.osaka-u.ac.jp

Yutaka Oda

e-mail: oda@mech.eng.osaka-u.ac.jp
Department of Mechanical Engineering,
Osaka University,
2-1, Yamada-oka, Suita,
Osaka 5650871, Japan

Yuta Egawa

Die Casting Engineering Department,
Toyota Motor Co. 1, Toyota-cho,
Toyota City 4718571, Japan
e-mail: yuta_egawa@mail.toyota.co.jp

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of the ASME for publication in the Journal of Turbomachinery. Manuscript received December 28, 2012; final manuscript received December 30, 2012; published online September 27, 2013. Editor: David Wisler.

J. Turbomach 136(5), 051001 (Sep 27, 2013) (9 pages) Paper No: TURBO-12-1252; doi: 10.1115/1.4023909 History: Received December 28, 2012; Revised December 30, 2012

This paper describes the experimental results of a new film cooling method that utilizes swirling coolant flow through circular and shaped film cooling holes. The experiments were conducted by using a scale-up model of a film-cooling hole installed on the bottom surface of a low-speed wind tunnel. Swirling motion of the film coolant was induced inside a hexagonal plenum using two diagonal impingement jets, which were inclined at an angle of α toward the vertical direction and installed in staggered positions. These two impingement jets generated a swirling flow inside the plenum, which entered the film-cooling hole and maintained its angular momentum until exiting the film-cooling hole. The slant angle of the impingement jets was changed to α = 0 deg, 10 deg, 20 deg, and 30 deg in the wind tunnel tests. The film cooling effectiveness on a flat wall was measured by a pressure sensitive paint (PSP) technique. In addition, the spatial distributions of the nondimensional concentration (or temperature) and flow field were measured by laser-induced fluorescence (LIF) and particle image velocimetry (PIV), respectively. In the case of a circular film-cooling hole, the penetration of the coolant jet into the mainstream was suppressed by the swirling motion of the coolant. As a result, although the coolant jet was deflected in the pitch direction, the film cooling effectiveness on the wall maintained a higher value behind the cooling hole over a long range. Additionally, the kidney vortex structure disappeared. For the shaped cooling hole, the coolant jet spread wider in the spanwise direction downstream. Thus, the pitch-averaged film cooling effectiveness downstream was 50% higher than that in the nonswirling case.

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Fig. 1

Geometries of film cooling holes

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Fig. 2

Structure of film cooling with swirling flow

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Fig. 3

Schematic layout of acetone LIF method

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Fig. 4

Film cooling effectiveness contours of circular hole with blowing ratio M = 0.5

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Fig. 5

Film cooling effectiveness contours of circular hole with blowing ratio M = 1.0

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Fig. 6

Spanwise-averaged film cooling effectiveness versus impingement jet angle (circular hole at M = 1.0)

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Fig. 7

Spanwise-averaged film cooling effectiveness

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Fig. 8

Film cooling effectiveness contours of shaped hole at blowing ratio M = 0.5

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Fig. 9

Film cooling effectiveness contours of shaped hole blowing ratio M = 1.0

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Fig. 10

Spanwise averaged film cooling effectiveness versus impingement jet angle (shaped hole at M = 1.0)

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Fig. 11

Spanwise-averaged film effectiveness at M = 1.0

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Fig. 12

Spanwise-averaged film effectiveness at M = 2.0

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Fig. 13

Spatial nondimensional concentration contours (circular hole at z/d = 0 section)

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Fig. 14

Cross section nondimensional concentration contours (circular hole, M = 1.0)

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Fig. 15

Spatial nondimensional concentration contours of a shaped hole at z/d = 0

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Fig. 16

Cross section nondimensional concentration contours (shaped hole at M = 1.0)

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Fig. 17

Time-averaged vorticity field of cylindrical film cooling hole at M = 1.0

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Fig. 18

Time-averaged velocity field of circular film cooling hole at M = 1.0

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Fig. 19

Time-averaged vorticity field of shaped film cooling hole at z/d = 0 section

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Fig. 20

Time-averaged vorticity field of shaped film cooling hole at M = 1.0



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