Skip to main content
Log in

Investigation of the Influence of Inclination Angle and Diffusion Angle on the Film Cooling Performance of Chevron Shaped Hole

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

Abstract

The film cooling performance of chevron holes with different inclination angles and exit lateral diffusion angles has been studied experimentally and numerically. The inclination angles include 35° and 55°. The exit lateral diffusion angles include 20° and 25°. The film cooling effectiveness, heat transfer coefficient and discharge coefficient were measured on a flat plate model by transient liquid crystal measurement technique under four blowing ratios. The results show that the large inclination angle reduces the film cooling effectiveness. The influence of diffusion angle has two aspects: the large diffusion angle leads to mainstream ingestion and decreases film cooling effectiveness at M=1.0 and 1.5; however, the large diffusion angle increases the film cooling effectiveness at high blowing ratio of 2.0, because the larger hole exit area decreases the normal momentum component of the film jet. The large inclination angle decreases the heat transfer coefficient in the right downstream region at M=0.5 and 1.0. The large diffusion angle enhances the heat transfer in the right downstream of the holes in M=0.5~1.5 conditions. The chevron hole with large inclination angle generally has the highest discharge coefficient.

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

Access this article

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

Instant access to the full article PDF.

Similar content being viewed by others

References

  1. Bunker R.S., A review of shaped hole turbine film cooling technology. ASME Journal of Heat Transfer, 2005, 127: 441–453.

    Article  Google Scholar 

  2. Goldstein R.J., Eckert E.R.G., Burggraf F. Effects of hole geometry and density on three-dimensional film cooling. International Journal of Heat & Mass Transfer. 1974, 17: 595–607.

    Article  Google Scholar 

  3. Gritsch M., Schulz A., Witting S. Adiabatic wall effectiveness measurements of film cooling holes with expanded exits. ASME Journal of Turbomachinery. 1998, 120: 549–556.

    Article  Google Scholar 

  4. Gritsch M., Schulz A., Wittig S., Heat transfer coefficient measurements of film-cooling holes with expanded exits, ASME Gas Turbine and Aeroengine Congress and Exihibition, Stockholm, Sweden, 98-GT-028, 1998.

    Google Scholar 

  5. Gräf L, Kleiser L. Flow-field analysis of anti-kidney vortex film cooling. Journal of Thermal Science. 2012, 21(1): 66–76.

    Article  ADS  Google Scholar 

  6. Thole K., Gritsch M., Schulz A., Witting S. Flowfield measurements for film cooling holes with expanded exits. ASME Journal of Turbomachinery. 1998, 120: 327–336.

    Article  Google Scholar 

  7. Wright L.M., McClain S.T., Clemenson M.D. Effect of density ratio on flat plate film cooling with shaped holes using PSP. ASME Journal of Turbomachinery. 2011, 133: 041011.

    Article  Google Scholar 

  8. Bunker R.S., Film cooling effectiveness due to discrete holes within a transverse surface slot, ASME Turbo Expo, Amsterdam, The Netherlands, GT2002-30178, 2002.

    Google Scholar 

  9. Khajehhasani S., Jubran B., Film cooling from novel sister shaped single-holes, ASME Turbo Expo, Dusseldorf, Germany, GT2014–25971, 2014.

    Book  Google Scholar 

  10. Li G., Chen Y., Kou Z., Zhang W., and Zhang G. Mechanism of film cooling with one inlet and double outlet hole injection at various turbulence intensities. International Journal of Turbo & Jet Engines. 2018, 35(1): 1–9.

    Article  ADS  Google Scholar 

  11. Sargison J.E., Guo S.M., Oldfield M.L.G., Lock G.D., A converging slot hole film-cooling geometry—part 1: low-speed flat-plate heat transfer and loss. ASME Journal of Turbomachinery, 2002, 124: 453–460.

    Article  Google Scholar 

  12. Liu C.L., Zhu H.R., Bai J.T. Experimental and numerical investigation on the film cooling of waist-shaped slot holes comparing with converging slot holes. ASME Journal of Turbomachinery. 2012, 134: 011021.

    Article  Google Scholar 

  13. Lee C.P., Brassfield S. R., Bunker R.S. Chevron film cooled wall. US, US7328580. 2008.

    Google Scholar 

  14. Liu J.S., Malak M.F., Tapia L.A., et al., Enhanced film cooling effectiveness with new shaped holes, ASME Turbo Expo, Glasgow, UK, GT2010-22774, 2010.

    Book  Google Scholar 

  15. Teng S., Han J.C., Poinsatte P.E. Effect of film-hole shape on turbine-blade film-cooling performance. AIAA Journal of Thermophysics and Heat Transfer. 2000, 5: 257–265.

    Google Scholar 

  16. Dittmar J., Schulz A., Wittig S. Adiabatic effectiveness and heat transfer coefficient of shaped film-cooling holes on a scaled guide vane pressure side model. International Journal of Rotating Machinery. 2004, 10: 345–354.

    Article  Google Scholar 

  17. Liu J.J., Bai T., et al. Leading edge film cooling enhancement for an inlet guide vane with fan-shaped holes. Journal of Thermal Science. 2010, 19(6): 514–518.

    Article  ADS  Google Scholar 

  18. Yuen C.H.N., Martinez-Botas R.F. Film cooling characteristics of a single hole at various streamwise angles: Part I. Effectiveness. International Journal of Heat & Mass Transfer. 2003, 46: 221–235.

    Article  Google Scholar 

  19. Kohli A., Bogard D., Effects of hole shape on film cooling with large angle injection, ASME Gas Turbine and Aeroengine Congress and Expo., Indianapolis, Indiana, USA, 99-GT-165, 1999.

    Google Scholar 

  20. Gritsch M., Colban W., Schar H. Effect of hole geometry on the thermal performance of fan-shaped film cooling holes. ASME Journal of Turbomachinery. 2005, 127: 718–725.

    Article  Google Scholar 

  21. Li G.C., Wang H.F., Zhang W., Kou Z., Xu R. Film cooling performance of a row of dual-fanned holes at various injection angles. Journal of Thermal Science. 2017, 26(5): 453–458.

    Article  ADS  Google Scholar 

  22. Haydt S.E., Lynch S., Lewis S.D. The effect of meter-diffuser offset on shaped film cooling hole adiabatic effectiveness. Journal of Turbomachinery. 2016, 139(9): 091012.

    Article  Google Scholar 

  23. Liu C.L., Liu J.L., Zhu H.R., Wu A.S. Film cooling sensitivity of laidback fanshape holes to variations in exit configuration and mainstream turbulence intensity. International Journal of Heat & Mass Transfer. 2015, 89: 1141–1154.

    Article  Google Scholar 

  24. Liu C.L., Zhu H.R., Wu A.S. Experimental investigation on the influence of inclination angle on the film cooling performance of diffuser shaped holes, ASME Turbo Expo. Seoul, South Korea, GT2016-56092. 2016.

    Google Scholar 

  25. Wei J.S., Zhu H.R., Liu C.L., Song H. Experimental study on the film cooling characteristics of the cylindrical holes embedded in sine-wave shaped trench, ASME Turbo Expo. Seoul, South Korea, GT2016-56856. 2016.

    Google Scholar 

  26. Liu C.L., Zhu H.R., Bai J.T., Xu D.C., Film cooling performance of converging-slot holes with different exitentry area ratios, Journal of Turbomachinery, 2009, 133: 186–192.

    Google Scholar 

  27. Vedula R.J., Metzger D. E., A method for the simultaneous determination of local effectiveness and heat transfer distributions in three temperature convection situations, ASME Gas Turbine and Aeroengine Congress and Exhibition, Orlando, Florida, USA, 91-GT-345, 1991.

    Google Scholar 

  28. Chambers A.C., Gillespie D.R.H., Ireland P.T., A novel transient liquid crystal technique to determine heat transfer coefficient distributions and adiabatic wall temperature in a three temperature problem, ASME Journal of Turbomachinery, 2003, 125: 538–546.

    Article  Google Scholar 

  29. Drost U., Bolcs A., Hoffs A., Utilization of the transient liquid crystal technique for film cooling effectiveness and heat transfer investigations on a flat plane and a turbine airfoil, ASME Gas Turbine and Aeroengine Congress and Exhibition, Orlando, Florida, USA, 97-GT-20, 1997.

    Google Scholar 

  30. Goldstein R.J., Eckert E.R.G., Ramsey J.W. Film cooling with injection through holes: adiabatic wall temperatures downstream of a circular hole. Journal of Engineering for Power. 1968, 90: 384–393.

    Google Scholar 

  31. Lutum E., Johnson B.V., Influence of the hole length-to-diameter ratio on film cooling with cylindrical holes, Journal of Turbomachinery, 1999, 121: 209–216.

    Article  Google Scholar 

Download references

Acknowledgements

Financial support from the National Basic Research Program of China “973” (Grant No. 2013CB035702)

Author information

Authors and Affiliations

Authors

Corresponding author

Correspondence to Huiren Zhu.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Fu, Z., Zhu, H., Liu, C. et al. Investigation of the Influence of Inclination Angle and Diffusion Angle on the Film Cooling Performance of Chevron Shaped Hole. J. Therm. Sci. 27, 580–591 (2018). https://doi.org/10.1007/s11630-018-1070-8

Download citation

  • Received:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11630-018-1070-8

Keywords

Navigation