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Analysis of Low-Pressure Turbine Nozzle Guide Vane Failure in an Aero Gas Turbine Engine: A Computational Approach

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Abstract

Failure of low-pressure turbine nozzle guide vane (NGV) in an aero gas turbine engine is analyzed using computational approach. Breakage in the cooling system of the nozzle guide vane reducing the cooling effectiveness is found to be the main cause of NGV failure. Microstructure analysis also shows severe oxidation due to high temperature experienced in service leading to erosion of the NGV.

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References

  1. V. Ganesan, Gas Turbines, 2nd edn. (TATA McGraw Hill, New York, 2009)

    Google Scholar 

  2. H. Cohen, G.F.C. Rogers, H.I.H. Saravanamuttoo, Gas Turbine Theory (Wiley, Hoboken, 1996)

    Google Scholar 

  3. J. Hour, B.J. Wicks, R.A. Antoniou, An investigation of fatigue failures of turbine blades in a gas turbine engine by mechanical analysis. J. Eng. Fail. Anal. 9(2), 201–211 (2002)

    Article  Google Scholar 

  4. H. Kazempour-Liacy, S. Abouali, M. Akbari-Garakani, Failure analysis of a first stage gas turbine blade. J. Eng. Fail. Anal. 18(1), 517–522 (2011)

    Article  Google Scholar 

  5. A.H. Lefebvre, GAS Turbine Combustion (CRC Press, Boca Raton, 1998)

    Google Scholar 

  6. S.K. Muduli, R.K. Mishra, R.K. Satpathy, S. Chandel, Effect of operating conditions on the performance parameters of a highly loaded annular combustor. Int. J. Turbo Jet Engine 32(1), 25–32 (2015). https://doi.org/10.1515/tjj-2014-0016

    Article  Google Scholar 

  7. R.K. Mishra, Influence of upstream flow distortion on the performance of an aero gas turbine combustor, in XIX International Symposium on Air Breathing Engines, Montreal, Canada (2009)

  8. R.K. Mishra, M.N. Bhat, R.D. Navindgi, T.K. Sampathkumaran, Effect of fuel-air ratio on the performance of a short annular aero gas turbine combustor, in 6th National Conference on Air Breathing Engines, Bangalore, India (2003)

  9. R.K. Mishra, Sunil Chandel, Soot formation and its effect in an aero gas turbine combustor. Int. J. Turbo Jet Engines (2016). https://doi.org/10.1515/tjj-2016-0062. ISSN (Online) 2191-0332

    Google Scholar 

  10. C.B. Meher-Homji, G. Gabriles, Gas turbine blade failures-causes, avoidance and trouble shooting, in Proceedings of 27th Turbomachinery Symposium (1995)

  11. R.K. Mishra, J. Thomas, K. Srinivasan, V. Nandi, R. Bhat, Failure analysis of nozzle guide vane of a low pressure turbine in an aero gas turbine engine. J. Fail. Anal. Prev. (2014). https://doi.org/10.1007/s11668-014-9858-7

    Google Scholar 

  12. N. Eliaz, G. Shemesh, R.M. Latanision, Hot corrosion in gas turbine components. J. Eng. Fail. Anal. 9(1), 31–43 (2002)

    Article  Google Scholar 

  13. Ali Rozati, Large Eddy Simulation of Leading Edge Film Cooling (Faculty of the Virginia Polytechnic Institute and State University, Blacksburg, 2007)

    Google Scholar 

  14. Carlo Carcasci, Bruno Facchini, A Numerical Procedure to Design Internal Cooling of Gas Turbine Stator Blades (DEF, S Stecco department of Energy engineering, Florence, 1996)

    Book  Google Scholar 

  15. D.G. Knost, Predictions and measurements of Film-cooling on the Endwall of a First stage vane (Virginia Polytechnic Institute and state University, Blacksburg, 2003)

    Google Scholar 

  16. R.J. Garde, Turbulent Flow, 2nd edn. (New Age International Publication, New Delhi, 2010)

    Google Scholar 

  17. G. Cerri, A. Giovannelli, L. Battisti, R. Fedrizzi, Advances in effusive cooling techniques of gas turbines. Appl. Therm. Eng. 27, 692–698 (2007)

    Article  Google Scholar 

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Acknowledgments

The authors are very grateful to the Chief Executive (airworthiness), CEMILAC, for his kind permission for publishing this paper.

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  1. Regional Centre for Military Airworthiness (Engines), CEMILAC, Bangalore, 560093, India

    D. Arul Kumaresan & R. K. Mishra

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  1. D. Arul Kumaresan
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  2. R. K. Mishra
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Correspondence to R. K. Mishra.

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Kumaresan, D.A., Mishra, R.K. Analysis of Low-Pressure Turbine Nozzle Guide Vane Failure in an Aero Gas Turbine Engine: A Computational Approach. J Fail. Anal. and Preven. 19, 504–510 (2019). https://doi.org/10.1007/s11668-019-00628-8

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  • DOI: https://doi.org/10.1007/s11668-019-00628-8

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