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Failure Analysis of High-Pressure Compressor Blade in an Aero Gas Turbine Engine

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Abstract

Failure of high-pressure compressor rotor blade in an aero gas turbine engine is analyzed to determine its root cause. Forensic and metallurgical investigations are carried out on the blade and failed parts. The failure of the platform ladder is found to the first in the chain of events that led to the compressor blade failure. The mode of failure in the blade is found to be fatigue and has originated from the damaged region on the leading edge caused by dislodgement of platform ladder. The failure has caused extensive damages in high-pressure compressor module and also in downstream turbine blades as a secondary effect.

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Authors and Affiliations

  1. Centre for Military Airworthiness and Certification, Bangalore, India

    R. K. Mishra

  2. Central Material Processing Laboratory, Hindustan Aeronautics Limited, Bangalore, India

    Vaishakhi Nandi & R. Raghavendra Bhat

Authors
  1. R. K. Mishra
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  2. Vaishakhi Nandi
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  3. R. Raghavendra Bhat
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Correspondence to R. K. Mishra.

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Mishra, R.K., Nandi, V. & Raghavendra Bhat, R. Failure Analysis of High-Pressure Compressor Blade in an Aero Gas Turbine Engine. J Fail. Anal. and Preven. 18, 465–470 (2018). https://doi.org/10.1007/s11668-018-0425-5

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  • DOI: https://doi.org/10.1007/s11668-018-0425-5

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