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Investigation of Compressor Failure in a Military Turbojet Engine

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Abstract

During altitude maneuver loud bang sound was observed followed by rapid winding down of engine rotation and jet pipe temperature. Compressor casing top half was found severely ruptured and broken into many pieces. On viewing through the ruptured area compressor rotor blades were found sheared at the root. Systematic investigation revealed that the failure of compressor casing was due to sudden overload. Analyzing the possible reasons of sudden overload it could be concluded that the rupture of compressor casing was most probably due to surge during the maneuvers. Remedial measures are suggested to address such failures.

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Acknowledgments

The authors are very grateful to Chief Executive (Airworthiness), CEMILAC and Executive Director, Hindustan Aeronautics Limited, Engine Division for their kind permission to present this paper. The authors are very thankful to the staff and engineers of Quality Assurance Group, Engine Division, Hindustan Aeronautics Limited, Bangalore and members of defect investigation team for their valuable suggestions and supports during this investigation.

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Authors and Affiliations

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

    R. K. Mishra

  2. Engine Division, Hindustan Aeronautics Limited, C V Raman Nagar, Bangalore, 560093, India

    Johney Thomas

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  1. R. K. Mishra
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  2. Johney Thomas
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Correspondence to R. K. Mishra.

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Mishra, R.K., Thomas, J. Investigation of Compressor Failure in a Military Turbojet Engine. J Fail. Anal. and Preven. 14, 443–449 (2014). https://doi.org/10.1007/s11668-014-9843-1

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  • DOI: https://doi.org/10.1007/s11668-014-9843-1

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