Skip to main content
SpringerLink
Log in

Influence of internal channel geometry of gas turbine blade on flow structure and heat transfer

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

Abstract

This paper presents the study of the influence of channel geometry on the flow structure and heat transfer, and also their correlations on all the walls of a radial cooling passage model of a gas turbine blade. The investigations focus on the heat transfer and aerodynamic measurements in the channel, which is an accurate representation of the configuration used in aeroengines. Correlations for the heat transfer coefficient and the pressure drop used in the design of internal cooling passages are often developed from simplified models. It is important to note that real engine passages do not have perfect rectangular cross sections, but include a corner fillets, ribs with fillet radii and a special orientation. Therefore, this work provides detailed fluid flow and heat transfer data for a model of radial cooling geometry which has very realistic features.

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. Metzger D. E., Larson D. E., Use of Melting Point Surface Coating for Local Convection Heat Transfer Measurements in Rectangular Channel Flows with 90-deg Turns, ASME Journal of Heat Transfer, Vol. 108, pp. 48–54, (1986)

    Article  Google Scholar 

  2. Kiml R., Mochizuki S., Murata A., Effects of Rib Arrangements on Heat Transfer and Flow Behavior in a Rectangular Rib-Roughened Passage: Application to Cooling of Gas Turbine Blade Trailing Edge, ASME Journal of Heat Transfer, Vol. 123, pp. 675–681, (2001)

    Article  Google Scholar 

  3. Arts T., Benocci C., Rambaud P., Experimental and Numerical Investigation of Flow and Heat Transfer in a Ribbed Square Duct, 3rd International Symposium on Integrating CFD and Experiments in Aerodynamics, U.S. Air Force Academy, Colorado, (2007)

    Google Scholar 

  4. http://www.ericka.eu, (2009-2014)

  5. Kaczynski P., Szwaba R., Doerffer P., Flaszynski P., Aerodynamic Enhancement in Inner Channel of Turbine Blade, Task Quarterly, Vol. 19, No 2, pp. 101–110 (2015)

    Google Scholar 

  6. Cakan, M., Aero-thermal Investigation of Fixed Rib-roughened Internal Cooling Passages, Ph.D. Thesis, Turbomachinery Department, Von Karman Institute for Fluid Dynamics, Brussels, (2000)

    Google Scholar 

  7. Irland P. T., Jones T. V., The Measurement of Local Heat Transfer Coefficients in Blade Cooling Geometries, AGARD Conference on Heat Transfer and Cooling in Gas Turbines, CP390 Paper 28, Bergen, (1985)

    Google Scholar 

  8. Jones T. V., Hippensteele S. A., High Resolution Heat Transfer Coefficient Maps Applicable to Compound Curve Surfaces Using Liquid Crystals in a Transient Wind Tunnel, NASA TM89855, (1988)

    Google Scholar 

  9. Vogel G., Graf A. B. A., Wolfersdorf J., Weigand B., A Novel Transient Heater-Foil Technique for Liquid Crystal Experiments on Film-Cooled Surfaces, ASME Journal of Turbomachinery, Vol. 125, pp. 529–537, (2003)

    Article  Google Scholar 

  10. Clifford R. J., Jones T. V., Dunne S. D., Techniques for Obtaining Detailed Heat Transfer Coefficient Measurements within Gas Turbine Blade and Vane Cooling Passages, ASME Paper 83-GT-58, Arizona, USA, (1983)

    Book  Google Scholar 

  11. Ireland, P.T., Neely, A.J., and Gillespie, D.R.H., Turbulent heat transfer measurements using liquid crystals, International Journal of Heat and Fluid Flow, Vol.: 20, Issue: 4, pp. 355–367, (1999)

    Article  Google Scholar 

  12. Szwaba R., Kaczynski P., Doerffer P., Telega J., Flow Structure and Heat Exchange Analysis in Internal Cooling Channel of Gas Turbine Blade, Journal of Thermal Science, Vol.25, No.4, pp. 336–341, (2016)

    Article  ADS  Google Scholar 

  13. Telega J., Doerffer P., Szwaba R., Kaczynski P., Parallelized Numerical Code For Derivation Of Heat Transfer Coefficient From Experimental Data, TASK Quarterly, Vol. 19, No. 2, pp. 197–205, (2015)

    Google Scholar 

Download references

Acknowledgments

The research leading to these results has received funding from the European Union Seventh Framework Programme (FP7/2007-2013) under Grant Agreement No. 233799 (ERICKA). Permission for publication is gratefully acknowledged by the authors.

Author information

Authors and Affiliations

  1. Institute of Fluid-Flow Machinery, Polish Academy of Sciences (IMP PAN), Fiszera 14, 80-952, Gdansk, Poland

    Ryszard Szwaba, Piotr Kaczynski, Janusz Telega & Piotr Doerffer

Authors
  1. Ryszard Szwaba
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Piotr Kaczynski
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Janusz Telega
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Piotr Doerffer
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Ryszard Szwaba.

Additional information

The research has received funding from the European Union Seventh Framework Programme (FP7/2007-2013) under Grant Agreement No. 233799 (ERICKA).

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Szwaba, R., Kaczynski, P., Telega, J. et al. Influence of internal channel geometry of gas turbine blade on flow structure and heat transfer. J. Therm. Sci. 26, 514–522 (2017). https://doi.org/10.1007/s11630-017-0968-x

Download citation

  • Received:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11630-017-0968-x

Keywords

Search

Navigation