Numerical Simulation of Hole Shapes Effect on Film Cooling Effectiveness and Aerodynamics Loss over Flat Plate

Ruo Ling Dong; Hong Hui Shi; Wei Chen; Xiao Dong Zhang

doi:10.4028/www.scientific.net/AMR.614-615.216

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 614-615Numerical Simulation of Hole Shapes Effect on Film...

Numerical Simulation of Hole Shapes Effect on Film Cooling Effectiveness and Aerodynamics Loss over Flat Plate

Abstract:

A numerical simulation was conducted to investigate the flow characteristics, film cooling effectiveness and aerodynamics loss over flat plate. Three types of shaped holes, separately, cylindrical hole, laterally diffused hole and converging-expanding hole were studied with 35°inclination angle and 0°compound angle. The inlet diameter of the hole in this paper is 12.7 mm, giving a L/D ratio of 3.5 at a mainstream velocity of 20m/s, turbulence intensity 2%, and temperature ratio to cooling jet 1.97, with blowing ratio M equaling to 0.5. Realizable k-ε turbulence model, standard wall function and SIMPLE method for pressure-velocity coupling were used .The coefficients η and ξ were calculated to analyze cooling effectiveness and aerodynamics loss. Both high film cooling effectiveness and low loss are found with laterally diffused hole. While optimizing the hole geometry in film cooling, cooling effectiveness and aerodynamics loss should been considered simultaneously.

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Periodical:

Advanced Materials Research (Volumes 614-615)

Pages:

216-221

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.614-615.216

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Online since:

December 2012

Authors:

Ruo Ling Dong, Hong Hui Shi, Wei Chen, Xiao Dong Zhang

Keywords:

Aerodynamics Loss, Film Cooling Effectiveness, Flow Field, Numerical Simulation, Shaped Holes

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References

[1] J. C. Han, S. Dutta and S. Ekkad: Gas turbine heat transferr and cooling technology", Xi'an Jiaotong University Publications Press, China 2005. (In Chinese)

Google Scholar

[2] R.J. Goldstein, E.R.G. Eckert and F.Burggraf: Int. J. Heat Mass Transfer. Vol.17(1974),p.595

Google Scholar

[3] M.B. Jovanović,H. C. de Lange and A. A. van Steenhoven: Int. J. Heat and Fluid Flow.Vol.29 (2008),p.377

Google Scholar

[4] M. Ni, H. R. Zhu, Y Qiu, et al: Gas Turbine Tech. Vol.18 (2005), p.25 (In Chinese)

Google Scholar

[5] R. S. Bunker: J. Heat Transfer. Vol. 127(2005), p.441

Google Scholar

[6] J. R. Pietrzyk, D. G. Bogard and M. E. Crawford: ASME J. Turbomach. Vol.112 (1990), p.437

Google Scholar

[7] D K Walters, J H Leylek: ASME J. Turbomach. Vol.119 (1997), p.437

Google Scholar

[8] C L Liu, H R Zhu and J T Bai: Journal of Aerospace Power. Vol. 23(2008), p.598 (in Chinese)

Google Scholar

[9] B A Haven, M K Kurosaka: Journal of Fluid Mehanics. Vol.352(1997), p: 27

Google Scholar