Skip to main content
SpringerLink
Log in

Visualization and quantitation of unsteadiness of film cooling near stagnation line of a double-wall cooled vane leading edge

  • Regular Paper
  • Published:
Journal of Visualization Aims and scope Submit manuscript

Abstract

Advanced double-wall cooling configuration has a large potential to reduce the highest heat load level in turbine vane leading-edge region both internally and externally. However, to date, the related knowledge of flow and thermal performances is still relatively scarce. In present work, the fluid-interaction-induced unsteady film cooling in leading-edge region of a double-wall cooled vane was of main concern, since that the cooling unsteadiness level is a crucial influencing factor of component durability. A time-resolved planar quantitative light sheet (QLS) system was designed to visualize the transient jet-behaviors and acquire the concentration-variations due to the unsteady film cooling jets. The atomizing dry-ice was validated as the suitable tracer particles, effectively avoiding the particle-blockages in the internal small-scale cooling-cavities of double-wall configuration. The effects of the amount and location of jet-ejections on the jet-trajectory, time-averaged film effectiveness and cooling unsteadiness levels in the stagnation zone of a double-wall cooling configuration with an actual vane geometry were deeply discussed. The relatively uniform time-averaged film coverage along the vane span can be found; however, the jets near the hub end-wall can produce the higher wall coverage fluctuation and the more unsteady jet-penetration. Increasing ejection-amount can change the jet-trajectory, as well as improve the time-averaged film effectiveness over the entire surface and the cooling unsteadiness level in some regions. The statistics of transient QLS data indicated that the unsteady film coverage and jet-penetration have the random feature. In general, besides the time-averaged cooling performances widely concerned in previous literature, the detailed knowledge of cooling unsteadiness level is also needed intensively, to design the more efficient double-wall cooling scheme in vane’s stagnation region, which has the improved component-durability as well.

Graphical abstract

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

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14
Fig. 15
Fig. 16
Fig. 17
Fig. 18
Fig. 19
Fig. 20

Similar content being viewed by others

References

  • Barigozzi G, Casarsa L, Pagnacco F, Rouina S (2019) Experimental investigation of the interaction between showerhead coolant jets and main flow. Exp Therm Fluid Sci 104:43–58

    Article  Google Scholar 

  • Bogard DG, Thole KA (2006) Gas turbine film cooling. AIAA J Propul Power 22(2):249–270

    Article  Google Scholar 

  • Bunker RS (2013) Gas turbine cooling: moving from macro to micro cooling. In: proceedings of ASME turbo expo, GT2013-94277

  • Fawcett RJ, Wheeler APS, He L, Taylor R (2012) Experimental investigation into unsteady effects on film cooling. ASME J Turbomach 134:021015

    Article  Google Scholar 

  • Freund O, Rehder HJ, Schaefer P, Roehle I, (2011) Experimental investigations on cooling air ejection at a straight turbine cascade using PIV and QLS. In: proceedings of ASME turbo expo, GT2011-45296

  • Gao Z, Han JC (2009) Influence of film-hole shape and angle on showerhead film cooling using PSP technique. ASME J Heat Transf 131:15–25

    Article  Google Scholar 

  • Goeckeler K, Terhaar S, Paschereit CO (2013) Residence time distribution in a swirling flow at non-reacting, reacting, and steam-diluted conditions. J Eng Gas Turbo and Power 136:041505

    Article  Google Scholar 

  • Han JC (2013) Fundamental gas turbine heat transfer. ASME J Therm Sci Eng Appl 5(2):021007

    Article  Google Scholar 

  • Han JC (2018) Advanced cooling in gas turbines 2016 Max Jakob memorial award paper. ASME J Heat Transf 140(11):113001

    Article  Google Scholar 

  • Huang X, Pu J, Wang J, Qu Y, He J (2020) Sensitivity analysis of internal layout and coating thickness to overall cooling performances of laminated cooling configurations with surface thermal barrier coatings. Appl Therm Eng 181:116020

    Article  Google Scholar 

  • Kim SH, Ahn KH, Park JS, Jung EY, Hwang K, Cho HH (2017) Local heat and mass transfer measurements for multi-layered impingement/effusion cooling: effects of pin spacing on the impingement and effusion plate. Int J Heat Mass Transf 105:712–722

    Article  Google Scholar 

  • Kim SH, Ahn KH, Jung EY, Park JS, Hwang K, Cho HH (2014) Total cooling effectiveness on laminated multilayer for impingement/effusion cooling system. In: proceedings of ASME turbo expo, GT2014–26692

  • Li SJ, Yang SF, Han JC (2014) Effect of coolant density on leading edge showerhead film cooling using the pressure sensitive paint measurement technique. ASME J Turbomach 136:775–791

    Article  Google Scholar 

  • Li W, Li X, Ren J, Jiang H (2017) Large eddy simulation of compound angle hole film cooling with hole length-to-diameter ratio and internal crossflow orientation effects. Int J Therm Sci 121:410–423

    Article  Google Scholar 

  • Li W, Li X, Ren J, Jiang H (2018) Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane. Appl Therm Eng 144:349–361

    Article  Google Scholar 

  • Liu CL, Zhao D, Zhai YN et al (2018) Investigations on the film cooling of counter inclined film-hole row structures for turbine vane leading edge. Int J Turbo Jet Eng 35:291–303

    Article  Google Scholar 

  • Murray AV, Ireland PT, Romero E (2018) Development of a steady-state experimental facility for the analysis of double-wall effusion cooling geometries. In: proceedings of ASME turbo expo, GT2018-75924

  • Nakamata C, Mimura F, Matsushita M, Yamane T, Fukuyama Y, Yoshida T (2007) Local cooling effectiveness distribution of an integrated impingement and pin fin cooling configuration. In: proceedings of ASME turbo expo, GT2007-27020

  • Ou S, Rivir RB (2001) Leading edge film cooling heat transfer with high free stream turbulence using a transient liquid crystal image method. Int J Heat Fluid Flow 22:614–623

    Article  Google Scholar 

  • Pu J, Wang W, Wang J, Wu W, Wang M (2020) Experimental study of free-stream turbulence intensity effect on overall cooling performances and solid thermal deformations of vane laminated end-walls with various internal pin-fin configurations. Appl Therm Eng 173:115232

    Article  Google Scholar 

  • Rouina S, Miranda M, Barigozzi G (2016) Experimental investigation of the unsteady flow behavior on a film cooling flat plate. Energy Procedia 101:726–733

    Article  Google Scholar 

  • Schroeder RP, Thole KA (2017) Thermal field measurements for a shaped hole at low and high freestream turbulence intensity. ASME J Turbomach 139:021012-1–21019

    Article  Google Scholar 

  • Sweeney PC, Rhodes JF (2000) An infrared technique for evaluating turbine airfoil cooling designs. ASME J Turbomach 122(1):170–177

    Article  Google Scholar 

  • Takeishi K, Oda Y, Seguchi J, Kozono S (2013) Effect of endwall film cooling upstream of an airfoil/endwall junction to suppress the formation of horseshoe vortex in asymmetric airfoil. In: proceedings of ASME turbo expo, GT2013-95385

  • Wright LM, Malak MF, Crites DC, Morris MC, Yelavkar V, Bilwani R (2014) Review of platform cooling technology for high pressure turbine blades. In: proceedings of ASME turbo expo, GT2014-26373

  • Zhang XD, Liu JJ, An BT (2016) The influences of element layout and coolant ejection angle on overall cooling effectiveness of laminated cooling configuration. Int J Heat Mass Transf 101:988–991

    Article  Google Scholar 

  • Zhou W, Pu J, Huang X, Wang J, Song W, Wu W (2021) Experimental investigation of inclination angle effect on unsteady film coverage of double-row staggered-holes at vane leading edge using time-resolved quantitative light sheet technique. Exp Therm Fluid Sci 123:110344

    Article  Google Scholar 

Download references

Acknowledgements

Funding was provided by Anhui Provincial Natural Science Foundation of China (Contract No. 2108085ME176) and Shenyang Aero-engine Institute of Aero Engine Corporation of China.

Author information

Authors and Affiliations

  1. Department of Thermal Science and Energy Engineering, University of Science and Technology of China, No. 96 Jinzhai Road, Hefei, 230027, Anhui, People’s Republic of China

    Jian Pu, Wen-li Zhou & Jian-hua Wang

  2. Shenyang Aero-Engine Institute of Aero Engine Corporation of China, No. 1 Wanlian Road, Shenyang, 110015, Liaoning, People’s Republic of China

    Wei Song

Authors
  1. Jian Pu
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Wen-li Zhou
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Jian-hua Wang
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Wei Song
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Jian Pu.

Additional information

Publisher's Note

Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.

Rights and permissions

Springer Nature or its licensor holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Pu, J., Zhou, Wl., Wang, Jh. et al. Visualization and quantitation of unsteadiness of film cooling near stagnation line of a double-wall cooled vane leading edge. J Vis 26, 113–129 (2023). https://doi.org/10.1007/s12650-022-00870-7

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s12650-022-00870-7

Keywords

Search

Navigation