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Research Papers: Jets, Wakes, and Impingment Cooling

Algebraic Anisotropic Turbulence Modeling of Compound Angled Film Cooling Validated by Particle Image Velocimetry and Pressure Sensitive Paint Measurements

[+] Author and Article Information
Xueying Li

e-mail: lixueying@mail.tsinghua.edu.cn

Hongde Jiang

Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received March 31, 2013; final manuscript received September 9, 2013; published online November 28, 2013. Assoc. Editor: Phillip M. Ligrani.

J. Heat Transfer 136(3), 032201 (Nov 28, 2013) (8 pages) Paper No: HT-13-1173; doi: 10.1115/1.4025411 History: Received March 31, 2013; Revised September 09, 2013

The complex structures in the film cooling flow field of gas turbines lead to the anisotropic property of the turbulent eddy viscosity and scalar diffusivity. An algebraic anisotropic turbulence model is developed aiming at a more accurate modeling of the Reynolds stress and turbulent scalar flux. In this study, the algebraic anisotropic model is validated by a series of in-house experiments for cylindrical film cooling with compound angle injection of 0, 45, and 90 deg. Adiabatic film cooling effectiveness and flow field are measured using pressure sensitive paint and particle image velocimetry techniques on film cooling test rig in Tsinghua University. Detailed analyses of computational simulations are performed. The algebraic anisotropic model gives a good prediction of the secondary vortices associated with the jet and the trajectory of the jet, therefore improves the prediction of the scalar field. On one hand, the anisotropic eddy viscosity improves the modeling of Reynolds stress and the predictive flow field. On the other hand, the anisotropic turbulent scalar-flux model includes the role of anisotropic eddy viscosity in modeling of scalar flux and directly improves the turbulent scalar flux prediction.

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Figures

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Fig. 1

Schematic diagram of the test rig

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Fig. 2

The spatial resolutions of 2D and 3D measurement (left-3D, right-2D)

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Fig. 3

Geometry of numerical computation

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Fig. 4

Grid for computation

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Fig. 5

Comparison of center line film cooling effectiveness with M = 0.5, β = 0 deg

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Fig. 6

Comparison of center line film cooling effectiveness with M = 1.0, β = 0 deg

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Fig. 7

X-vorticity distributions at X/D = 3 and X/D = 5 (compound angle 45 deg)

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Fig. 8

X-vorticity distributions at X/D = 3 and X/D = 5 (compound angle 90 deg)

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Fig. 9

Normalized velocity distribution at Z/D = 0 (compound angle 45 deg)

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Fig. 10

Normalized velocity distribution at Z/D = 0 (compound angle 90 deg)

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Fig. 11

Surface contour of adiabatic film cooling effectiveness (M = 0.5)

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Fig. 12

Lateral distribution of film cooling effectiveness for all three geometries

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