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Thermophysics and Aeromechanics

, Volume 23, Issue 5, pp 721–734 | Cite as

Numerical approach to new tangential slot effect on film cooling effectiveness over asymmetrical turbine blade

  • Z. Senouci
  • M. BenabedEmail author
Article

Abstract

The focus of this numerical study is to conceive a new basic film cooling configuration in order to increase film cooling effectiveness, especially at the leading edge zone between the injection holes where cooling is mostly needed. The new configuration, resulting from the tangential slot configuration and especially adapted to the leading edge of an asymmetrical blade, is compared to the uniform slot configuration. Three alternatives geometries were proposed and numerically tested to find the configuration that provides the best film cooling effectiveness. The simulation is conducted at a fixed density ratio of 1.0 and a blowing ratio of 0.7. A new parameter, Rc, is defined to measure the rate of blade coverage by the film cooling. The outcomes of the numerical results indicate that the three proposed configurations allow better thermal protection because of their higher film cooling coverage. At suction side, the new configurations provide a better film cooling coverage than the baseline case. The minimal improvement is at approximately 34%, with a light superiority of case 1. At pressure side, the use of the tangential slot is especially interesting for the allowed minimum adiabatic effectiveness values between 0.3 and 0.5.

Key words

film cooling tangential slot coverage ratio SST turbulence model 

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References

  1. 1.
    K. Wieghardt, Hot air discharge for deicing, AAF Translation F-Ts 919-Re, August 1946, Wright Field, Original in Deutsche Luftfahrtforschung: Über das Ausblasen von Warmluft für Enteiser, Forschungs-bericht Nr. 1900, Zentrale für Wissenschaftliches Berichtswesen.Google Scholar
  2. 2.
    S. Papell and A.M. Trout, Experimental investigation of air-film cooling applied to an adiabatic wall by means of an axially discharging slot, NASA Tech. Note TN D-9, 1959.Google Scholar
  3. 3.
    J.E. Hatch and S.S. Papell, Use of theoretical flow model to correlate data for film cooling or heating on adiabatic wall by tangential injection of gases of different fluid properties, NASA Tech. Note TN-130, 1959, P. 1–44.Google Scholar
  4. 4.
    J.P. Hartnett, R.C. Birkebak, and E.R.G. Eckert, Velocity distributions, temperature distributions, effectiveness, and heat transfer for air injected through a tangential slot into a turbulent boundary layer, Trans. ASME, Ser. C, J. Heat Transfer, 1961, Vol. 83, No. 3, P. 293–305.CrossRefGoogle Scholar
  5. 5.
    R.A. Seban, Heat transfer and effectiveness for a turbulent boundary layer with tangential fluid injection, Trans. ASME, Ser. C, J. Heat Transfer, 1960, Vol. 82, No. 4, P. 303–312.CrossRefGoogle Scholar
  6. 6.
    E. Redeker and D.S. Miller, in: M.A. Saad and J.A. Miller (Eds.), Proc. 1966 Heat Transfer and Fluid Mechanics Institute, Stanford Univ. Press, Stanford, California, 1966.Google Scholar
  7. 7.
    K.A. Juhany, M.L. Hunt, and J.M. Sivo, Influence of injectant Mach number and temperature on super-sonic film cooling, J. Thermophys. Heat Transfer, 1994, Vol. 8, No. 1, P. 59–67.CrossRefGoogle Scholar
  8. 8.
    S.C. Kacker, B.R. Pai, J.H. Whitelaw, Progress in heat and mass transfer / T.F. Irvine, Jr., W. Ibele, J.P. Hartnett, and R.J. Goldstein, eds. N.Y.: Macmillan (Pergamon), 1969. Vol. 2. P. 163–186.Google Scholar
  9. 9.
    S.C. Kacker and J.H. Whitelaw, The dependence of the impervious-wall effectiveness of a two-dimensional wall jet on the thickness of the upper-lip boundary-layer, Int. J. Heat Mass Transfer, 1967, Vol. 10, P. 623–624.CrossRefGoogle Scholar
  10. 10.
    S.C. Kacker, W.B. Nicoll, and J.H. Whitelaw, Dept. Mech. Engr. Imperial College, London, 1967, Rep. TWF/TN/30.Google Scholar
  11. 11.
    S.V. Patankar, D.B. Spalding, and J.H. Whitelaw, Heat and mass transfer in boundary layers, Morgan-Grampian Press, London, 1967.Google Scholar
  12. 12.
    D.E. Metzger, R.T. Baltzer, D.I. Takeuchi, and P.A. Kuenstler, Heat transfer to film cooled combustion liners, ASME Paper No. 72-WA/HT-32, 1972.Google Scholar
  13. 13.
    S. Wittig, G. Bittlinger, and A. Shulz, Film cooling effectiveness and heat transfer coefficients for slot injection at high blowing ratios, ASME Paper No. 94-GT-182, 1994.Google Scholar
  14. 14.
    R. Arnold, S. Suslov, and O.J. Haidn, Experimental investigation of film cooling with tangential slot injection in a LOX/CH4 subscale rocket combustion chamber, in: 26th Int. Symp. on Space Technology and Sci. (ISTS), 2008, Vol. 7, No. 26, P. 81–86.Google Scholar
  15. 15.
    R.S. Bunker, A review of shaped hole turbine cooling technology, ASME J. Heat Transfer, 2005, Vol. 127, P. 441–453.CrossRefGoogle Scholar
  16. 16.
    S. Ardey and L. Fottner, Flow field measurements on a large scale turbine cascade with leading edge film cooling by two rows of holes, ASME Paper No. 1997-GT-524, P. 1–9.Google Scholar
  17. 17.
    S. Ardey and L. Fottner, A systematic experimental study on the aerodynamics of leading edge film cooling on a large scale high pressure turbine cascade, ASME Paper No. 1998-GT-434.Google Scholar
  18. 18.
    ANSYS CFX 10.0 Documentations, 2005, P. 164–166.Google Scholar
  19. 19.
    D. Bohn and K. Kusterer, Aerothermal investigation of mixing flow phenomena in case of radially inclined ejection holes at the leading edge, ASME J. Turbo Machinery, 2000, Vol. 122, P. 334–339.CrossRefGoogle Scholar
  20. 20.
    D. Lakehal, G. Theodoridis, and W. Rodi, Three dimensional flow and heat transfer calculations of film cooling at the leading edge of asymmetrical turbine blade model, Int. J. Heat Fluid Flow, 2001, Vol. 22, P. 113–122.CrossRefGoogle Scholar
  21. 21.
    F.R. Menter, Zonal two-equation k-ω turbulence model for aerodynamic flows, AIAA Paper 93-2906, 1993, P. 1–21.Google Scholar
  22. 22.
    S. Friedrichs, H.P. Hodson, and W.N. Dawes, Distribution of film-cooling effectiveness on a turbine endwall measured using the ammonia and diazo technique, ASME J. Turbomachinery, 1995, Vol. 118, P. 613–621.CrossRefGoogle Scholar

Copyright information

© Pleiades Publishing, Ltd. 2016

Authors and Affiliations

  1. 1.University of Science and TechnologiesOranAlgeria

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