Skip to main content
SpringerLink
Log in

Research on cooling effectiveness in stepped slot film cooling vane

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

Abstract

As one of the most important developments in air cooling technology for hot parts of the aero-engine, film cooling technology has been widely used. Film cooling hole structure exists mainly in areas that have high temperature, uneven cooling effectiveness issues when in actual use. The first stage turbine vanes of the aero-engine consume the largest portion of cooling air, thereby the research on reducing the amount of cooling air has the greatest potential. A new stepped slot film cooling vane with a high cooling effectiveness and a high cooling uniformity was researched initially. Through numerical methods, the affecting factors of the cooling effectiveness of a vane with the stepped slot film cooling structure were researched. This paper focuses on the cooling effectiveness and the pressure loss in different blowing ratio conditions, then the most reasonable and scientific structure parameter can be obtained by analyzing the results. The results show that 1.0 mm is the optimum slot width and 10.0 is the most reasonable blowing ratio. Under this condition, the vane achieved the best cooling result and the highest cooling effectiveness, and also retained a low pressure loss.

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. Han J C, Dutta S, Ekkad S, (2012), Gas turbine heat transfer and cooling technology, Florida: CRC Press.

    Google Scholar 

  2. Eckert E. R. G., Eriksen V. L., Goldstein R. J., Ramsey J. W., (1970), Film cooling following injection through inclined circular tubes, Israel Journal of Technology, Vol. 8(1-2), pp. 145–154.

    Google Scholar 

  3. Sinha A. K., Bogard D. G., Crawford M. E., (1991), Film-Cooling Effectiveness Downstream of a Single Row of Holes With Variable Density Ratio, Journal of Turbomachinery, Vol. 113(3), pp. 442–449.

    Article  Google Scholar 

  4. Foster N. W., Lampard D., (1975), Effects of Density and Velocity Ratio on Discrete Hole Film Cooling, AIAA Journal, Vol. 13(8), pp. 1112–1114.

    Article  ADS  Google Scholar 

  5. Bons J. P., Mac Arthur C. D., Rivir R. B., (1996) The Effect of High Free-Stream Turbulence on Film Cooling Effectiveness. ASME Journal of Turbomachinery, Vol. 118(4), pp. 814–825.

    Article  Google Scholar 

  6. Kohli A., Bogard D. G., (1998), Effect of Very High Free-Stream Turbulence on the Jet-Mainstream Interaction in a Film Cooling Flow, ASME Journal of Turbomachinery, Vol. 120, pp. 785–790.

    Article  Google Scholar 

  7. Goldstein R. J., Eckert E. R. G., Burggraf F., (1974), Effects of hole geometry and density on three-dimensional film cooling, Internal Journal of Heat and Mass Transfer, Vol. 17(5), pp. 595–607.

    Article  Google Scholar 

  8. Burd S. W., Kaszeta R. W., Simon T. W., (1998), Measurements in Film Cooling Flows:Hole’s L/D and Turbulence Intensity Effects, ASME Journal of Turbomachinery, Vol. 120(4), pp. 791–798.

    Article  Google Scholar 

  9. Kim H. K., Moffat R. J., Kays, W. M., (1979), Heat transfer to a full-coverage film-cooled surface with compound-angle (30 deg and 45 deg) hole injection, Stanford Univ. Report.

    Google Scholar 

  10. Lee K. D., Kim K. Y., (2014), Film cooling performance of cylindrical holes embedded in a transverse trench, Numerical Heat Transfer, Part A: Applications, Vol. 65(2), pp. 127–143.

    Article  ADS  Google Scholar 

  11. Singh K., Premachandran B., Ravi M. R., (2015), A Numerical Study on the 2D Film Cooling of a Flat Surface, Numerical Heat Transfer, Part A: Applications, Vol. 67(6), pp. 673–695.

    Article  ADS  Google Scholar 

  12. Denton J D, Xu L, (1990) The trailing edge loss of transonic turbine blades, Journal of Turbomachinery, Vol. 112(2), pp. 277–285.

    Article  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, Beihang University, Xueyuan Road, 37, 100191, Beijing, China

    Yulong Li, Hong Wu, Feng Zhou & Chengjun Rong

Authors
  1. Yulong Li
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Hong Wu
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Feng Zhou
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Chengjun Rong
    View author publications

    You can also search for this author in PubMed Google Scholar

Additional information

This study was supported by funds form National natural science foundation of China (Grant No. 50976008).

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Li, Y., Wu, H., Zhou, F. et al. Research on cooling effectiveness in stepped slot film cooling vane. J. Therm. Sci. 25, 273–279 (2016). https://doi.org/10.1007/s11630-016-0860-0

Download citation

  • Received:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11630-016-0860-0

Keywords

Search

Navigation