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Research Papers

Film Cooling Modeling of Turbine Blades Using Algebraic Anisotropic Turbulence Models

[+] Author and Article Information
Xueying Li

Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: lixueying@mail.tsinghua.edu.cn

Jing Ren, Hongde Jiang

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

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 14, 2014; final manuscript received July 20, 2014; published online August 26, 2014. Editor: Ronald Bunker.

J. Turbomach 136(11), 111006 (Aug 26, 2014) (9 pages) Paper No: TURBO-14-1140; doi: 10.1115/1.4028174 History: Received July 14, 2014; Revised July 20, 2014

The complex structures in the flow field of gas turbine film cooling increase the anisotropy of turbulence making it difficult to accurately compute turbulent eddy viscosity and scalar diffusivity. An algebraic anisotropic turbulence model is developed while aiming at a more accurate modeling of the Reynolds stress and turbulent scalar-flux. In this study, the algebraic anisotropic model is validated by two in-house experiments. One is a leading edge with showerhead film cooling and the other is a vane with full coverage film cooling. Adiabatic film cooling effectiveness under different blowing ratios, density ratios, and film cooling arrangements were measured using pressure sensitive paint (PSP) technique. Four different turbulence models are tested and detailed analyses of computational simulations are performed. Among all the turbulence models investigated, the algebraic anisotropic model shows better agreement with the experimental data qualitatively and quantitatively. The algebraic anisotropic model gives a good prediction of the vortex strength and turbulence mixing of the jet, therefore improves the prediction of the scalar field.

Copyright © 2014 by ASME
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References

Figures

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Fig. 1

Wind tunnel of the experiment

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Fig. 2

Schematic diagram of the test section

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Fig. 3

Schematic of leading edge model

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Fig. 4

Grid for computation

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Fig. 5

Averaged adiabatic film cooling effectiveness (D.R = 1.0, M = 1.3)

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Fig. 6

Averaged adiabatic film cooling effectiveness (D.R = 1.5, M = 1.3)

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Fig. 7

Geometry of the test vane

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Fig. 8

The solution domain

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Fig. 10

Averaged adiabatic film cooling effectiveness for case A: (a) M = 0.5 and (b) M = 0.75

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Fig. 11

Averaged adiabatic film cooling effectiveness for case B: (a) M = 0.75 and (b) M = 1.0

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Fig. 12

Film cooling effectiveness on suction side of case A (M = 0.5)

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Fig. 13

Film cooling effectiveness on pressure side of case A (M = 0.5)

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Fig. 14

Film cooling effectiveness on suction side of case B (M = 1.5)

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Fig. 15

Film cooling effectiveness on pressure side of case B (M = 1.5)

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Fig. 16

Kinetic energy in the midspan passage of case B (M = 1.5)

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