Skip to main content
SpringerLink
Log in

Investigation on cooling effectiveness and aerodynamic loss of a turbine cascade with film cooling

  • Published:
Journal of Thermal Science Aims and scope Submit manuscript

Abstract

This paper describes the numerical study on film cooling effectiveness and aerodynamic loss due to coolant and main stream mixing for a turbine guide vane. The effects of blowing ratio, mainstream Mach number, surface curvature on the cooling effectiveness and mixing loss were studied and discussed. The numerical results show that the distributions of film cooling effectiveness on the suction surface and pressure surface at the same blowing ratio (BR) are different due to local surface curvature and pressure gradient. The aerodynamic loss features for film holes on the pressure surface are also different from film holes on the suction surface.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

References

  1. Goldstein, R. J., Eckert, E. R. G., and Burggraf, F., (1974), Effects of Hole Geometry and Density on Three-Dimensional Film Cooling, International Journal of Heat and Mass Transfer, Vol.17, pp. 595–607.

    Article  Google Scholar 

  2. Bunker, R.S., (2005), A Review of Shaped Hole Turbine Film-Cooling Technology, ASME Journal of Heat Transfer, Vol.127, No.2, pp.441–457.

    Article  Google Scholar 

  3. Kusterer, K., Tekin, N., Kasiri, A., Bohn, D., Sugimoto, T., Tanaka, R., and Kazari, M., (2013), Highest Efficient Film Cooling by Improved Nekomimi Film Cooling - Part 2: Hot Gas Flow Conditions, ASME paper GT2013-95042, Proceedings of ASME Turbo Expo 2013, June 3–7, San Antonio, Texas, USA.

    Google Scholar 

  4. Bunker, R. S., (2010), Film Cooling: Breaking the Limits of the Diffusion Shaped Hole, Heat Transfer Research, Vol.41, No.6, pp.627–650.

    Article  Google Scholar 

  5. Haller, B. R. and Camus, J. J., (1984) Aerodynamic Loss Penalty Produced by Film Cooling Transonic Turbine Vanes, ASME Journal of Engineering for Gas Turbines and Power, Vol.106, No.1, pp.198–205.

    Article  Google Scholar 

  6. Day, C. R. B., Oldfield, M. L. G., and Lock, G. D., (2000) Aerodynamic Performance of an Annular Cascade of Film Cooled Nozzle Guide Vanes under Engine Representative Conditions, Experiments in Fluids, Vol.29, No. 2, pp.117–129.

    Article  ADS  Google Scholar 

  7. Gomes, R. A., (2012), Aerothermodynamics of a High- Pressure Turbine Vane with Very High Loading and Vortex Generators, ASME Journal of Turbomachinery, Vol.134, 011020.

    Article  Google Scholar 

  8. Friedrichs, S., and Hodson, H. P., (1997), Aerodynamic Aspects of Endwall Film-Cooling, ASME Journal of Turbomachinery, Vol.119, No.4, pp.786–793.

    Article  Google Scholar 

  9. Colban, W., and Thole, K., (2007), Influence of Hole Shape on the Performance of a Turbine Vane Endwall Film-cooling Scheme, International Journal of Heat and Fluid Flow, Vol.28, No.3, pp.41–356.

    Article  Google Scholar 

  10. Rehder, H. J., (2012), Investigation of Trailing Edge Cooling Concepts in a High Pressure Turbine Cascade-Aerodynamic Experiments and Loss Analysis, ASME Journal of Turbomachinery, Vol.134, No.5, 051029.

    Article  Google Scholar 

  11. Schobeiri, M. T., and Pappu, K., (1999), Optimization of Trailing Edge Ejection Mixing Losses: A Theoretical and Experimental Study, ASME Journal of Fluid Engineering, Vol.121, No.1, pp.118–125.

    Article  Google Scholar 

  12. Rezasoltani, M., Lu, K., Schobeiri, M. T., and Han, J. C. (2015), A Combined Experimental and Numerical Study of the Turbine Blade Tip Film Cooling Effectiveness Under Rotation Condition, ASME Journal of Turbomachinery, Vol.137, No.5, 051009.

    Article  Google Scholar 

  13. Abdelfattah, S. A., and Schobeiri, M. T. (2010), Experimental and Numerical Investigations of Aerodynamic Behavior of a Three-Stage HP-Turbine at Different Operating Conditions, ASME paper GT2010-23564, Proceedings of ASME Turbo Expo 2010, June 14–18, 2010, Glasgow, Scotland.

    Google Scholar 

  14. Liao, G., Wang, X., Li, J., and Zhang, F. (2014), Effects of Curvature on the Film Cooling Effectiveness of Double-Jet Film Cooling, ASME paper GT2014-26263, Proceedings of ASME Turbo Expo 2014, June 16–20, Dü sseldorf, Germany.

    Google Scholar 

  15. Walters, D. K., and Leylek, J. H. (2000), Impact of filmcooling jets on turbine aerodynamic losses, ASME Journal of Turbomachinery, 122(3), 537–545.

    Article  Google Scholar 

  16. Ito, S., Eckert, E. R. G., and Goldstein, R. J. (1980), Aerodynamic Loss in a Gas Turbine Stage with Film Cooling, ASME Journal of Engineering for Gas Turbines and Power, vol.102, No.4, pp.964–970.

    Article  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. Institute of Engineering Thermophysics, Chinese Academy of Sciences, 11 Beisihuan West Road, Beijing, 100190, China

    Jianjun Liu, Xiaochun Lin, Xiaodong Zhang & Baitao An

  2. School of Physics, University of Chinese Academy of Sciences, 19A Yuquan Road, Beijing, 100049, China

    Xiaochun Lin

Authors
  1. Jianjun Liu
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Xiaochun Lin
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Xiaodong Zhang
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Baitao An
    View author publications

    You can also search for this author in PubMed Google Scholar

Additional information

This research was financially supported by the National Natural Science Foundation of China through Grant No. 51336007

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Liu, J., Lin, X., Zhang, X. et al. Investigation on cooling effectiveness and aerodynamic loss of a turbine cascade with film cooling. J. Therm. Sci. 25, 50–59 (2016). https://doi.org/10.1007/s11630-016-0833-3

Download citation

  • Received:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11630-016-0833-3

Keywords

Search

Navigation