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Analysis of the influence of cooling hole arrangement on the protection of a gas turbine combustor liner

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Abstract

Numerical investigations of an industrial gas turbine combustor were conducted in this paper. The studied combustion chamber has a high degree of geometrical complexity related to the injection system as well as the cooling system which consists of thousands of small holes (about 3390 holes) bored on the liner walls. The main aim of this study was to propose modifications into the liner cooling system that can enhance the protection of this critical component. The calculations were carried out using the industrial CFD code fluent 6.3. It was shown that the addition of rows of cooling holes in the primary zone of the liner leads to a reduction of the maximum liner metal temperature of 33%. Nevertheless, this modification causes an increase of the maximum gas temperature at the outlet of the combustion chamber of 12% which could be harmful to the turbine vanes. It was also shown that this increase can be controlled by the suppression of rows of cooling holes in the dilution zone.

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References

  1. Rajendran R (2012) Gas turbine coatings—an overview. Eng Fail Anal 26:355–369

    Article  Google Scholar 

  2. Li L, Peng XF, Liu T (2006) Combustion and cooling performance in an aero-engine annular combustor. Appl Therm Eng 26:1771–1779

    Article  Google Scholar 

  3. Ben Sik Ali A, Kriaa W, Mhiri H, Bournot P (2012) Numerical investigations of cooling holes system role in the protection of the walls of a gas turbine combustion chamber. Heat Mass Transf 48(5):779–788

    Article  ADS  Google Scholar 

  4. Kim KM, Yun N, Jeon YH, Lee DH, Cho HH, Kang SH (2010) Conjugated heat transfer and temperature distributions in a gas turbine combustion liner under base-load operation. J Mech Sci Technol 24(9):1939–1946

    Article  Google Scholar 

  5. Kim KM, Jeon YH, Yun N, Lee DH, Cho HH (2011) Thermo-mechanical life prediction for material lifetime improvement of an internal cooling system in a combustion liner. Energy 36:942–949

    Article  Google Scholar 

  6. Lv F, Li Q, Fu G (2010) Failure analysis of an aero-engine combustor liner. Eng Fail Anal 17:1094–1101

    Article  Google Scholar 

  7. Moussavi Torshizi SE, Ebrahimi M (2013) Failure analysis of gas turbine transition pieces, leading to a solution for prevention. Eng Fail Anal 32:402–411

    Article  Google Scholar 

  8. Mazur Z, Hernandez-Rossette A, Garcia-Illescas R, Luna-Ramirez A (2008) Failure analysis of a gas turbine nozzle. Eng Fail Anal 15:913–921

    Article  Google Scholar 

  9. Vardar N, Ekerim A (2007) Failure analysis of gas turbine blades in a thermal power plant. Eng Fail Anal 14:743–749

    Article  Google Scholar 

  10. Kim KM, Park JS, Lee DH, Lee TW, Cho HH (2011) Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages. Eng Fail Anal 18:1212–1222

    Article  Google Scholar 

  11. Naeem M (2009) Implications of day temperature variation for an aero-engine’s HP turbine-blade’s creep life-consumption. Aerosp Sci Technol 13:27–35

    Article  Google Scholar 

  12. Lefebvre AH (1998) GAS turbine combustion, combustion: an international series. McGraw-Hill series in energy, combustion, and environment, 2nd edn. CRC Press, London

  13. Hasann R, Puthukkudi A (2013) Numerical study of effusion cooling on an adiabatic flat plate. Propul Power Res 2(4):269–275

    Article  Google Scholar 

  14. Kim KM, Song J, Park JS, Lee S, Cho HH (2012) Material design of a film cooling system using experimental heat transfer data. Int J Heat Mass Transf 55:6278–6284

    Article  Google Scholar 

  15. Kim KM, Yun N, Jeon YH, Lee DH, Cho HH (2010) Failure analysis in after shell section of gas turbine combustion liner under base-load operation. Eng Fail Anal 17:848–856

    Article  Google Scholar 

  16. Andrei L, Andreini A, Bianchini C, Caciolli G, Facchini B, Mazzei L, Picchi A, Turrini F (2014) Effusion cooling plates for combustor liners: experimental and numerical investigations on the effect of density ratio. Energy Proc 45:1402–1411

    Article  Google Scholar 

  17. Chengfeng Y, Jingzhou Z (2012) Influence of multi-hole arrangement on cooling film development. Chin J Aeronaut 25:182–188

    Article  Google Scholar 

  18. Berger S, Richard S, Staffelbach G, Duchaine F, Gicquel L (2015) Aerothermal prediction of an aeronautical combustion chamber based on the coupling of large eddy simulation, solid conduction and radiation solvers, in volume 5A: heat transfer: V05AT10A007

  19. Andreini A, Facchini B, Mazzei L, Bellocci L, Turrini F (2014) Assessment of aero-thermal design methodology for effusion cooled lean burn annular combustors. In: Proceedings of ASME turbo expo 2014 turbine technical conference expo

  20. Mercier E, Tesse L, Savary N (2006) 3D full predictive thermal chain for gas turbine. In: 25th international congress of the aeronautical sciences

  21. Mazzei L, Andreini A, Facchini B, Bellocci L (2016) A 3D coupled approach for the thermal design of aero-engine combustor liners, volume 5B: heat transfer: V05BT17A009

  22. Da Soghe R, Bianchini C, Andreini A, Mazzei L, Riccio G, Marini A (2015) Metal temperature prediction of a dry low NO x class flame tube by computational fluid dynamics conjugate heat transfer approach. J Eng Gas Turbines Power 138(3):31501

    Article  Google Scholar 

  23. Da Soghe R, Bianchini C, Andreini A, Mazzei L, Riccio G, Marini A, Ciani A (2015) Thermofluid dynamic analysis of a gas turbine transition-piece. J Eng Gas Turbines Power 137(6):62602

    Article  Google Scholar 

  24. Mc Bride BJ, Gordon S, Reno M (1993) Coefficient for calculating thermodynamic and transport properties of individual species. Report TM-4513, NASA

  25. Launder BE, Spalding DB (1972) Lectures in mathematical models of turbulence. Academic Press, London

    MATH  Google Scholar 

  26. Frassoldati A, Frigerio S, Colombo E, Inzolib F, Faravelli T (2005) Determination of NO x emissions from strong swirling confined flames with an integrated CFD-based procedure. Chem Eng Sci 60(11):2851–2869

    Article  Google Scholar 

  27. Yang W, Zhang J (2008) Simulation of swirling turbulent combustion in the TECFLAM combustor. Comput Chem Eng 32(10):2280–2289

    Article  Google Scholar 

  28. Yang W, Zhang J (2009) Simulation of methane turbulent swirling flame in the TECFLAM combustor. Appl Math Model 33(6):2818–2830

    Article  Google Scholar 

  29. Magnussen BF, Hjertager BH (1976) On mathematical models of turbulent combustion with special emphasis on soot formation and combustion. In: 16th symposium (international) on combustion. The Combustion Institute

  30. ANSYS FLUENT Theory Guide, ANSYS, Inc., Release 14.0, 2011

  31. Saqr KM, Aly HS, Sies MM, Abdul WM (2011) Implementation of the eddy dissipation model of turbulent non-premixed combustion in Open FOAM. Int Commun Heat Mass 38:363–367

    Article  Google Scholar 

  32. Tsioumanis N, Brammer JG, Hubert J (2011) Flow processes in a radiant tube burner: combusting flow. Energy Convers Manag 52:2667–2675

    Article  Google Scholar 

  33. Chandrasekhar S (1960) Radiative transfer. Dover, New York

    MATH  Google Scholar 

  34. Leuckel W, Fricker N (1976) The characteristics of swirl-stabilized natural gas flames. Part I: different flame types and their relation to flow and mixing patterns. J Inst Fuel 49:103–112

    Google Scholar 

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Authors and Affiliations

  1. Unité de Thermique et Thermodynamique des Procédés Industriels, Ecole Nationale d’Ingénieurs de Monastir, Rue Ibn El Jazzar, 5000, Monastir, Tunisia

    Ahlem Ben Sik Ali, Wassim Kriaa & Hatem Mhiri

  2. IUSTI, UMR CNRS 6595, Technopôle de Château-Gombert, 5 Rue Enrico Fermi, 13013, Marseille, France

    Philippe Bournot

Authors
  1. Ahlem Ben Sik Ali
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  2. Wassim Kriaa
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  3. Hatem Mhiri
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  4. Philippe Bournot
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Correspondence to Ahlem Ben Sik Ali.

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Ben Sik Ali, A., Kriaa, W., Mhiri, H. et al. Analysis of the influence of cooling hole arrangement on the protection of a gas turbine combustor liner. Meccanica 53, 2257–2271 (2018). https://doi.org/10.1007/s11012-018-0824-4

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  • DOI: https://doi.org/10.1007/s11012-018-0824-4

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