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Journal of Failure Analysis and Prevention

, Volume 14, Issue 3, pp 296–302 | Cite as

Fatigue Failure of LP Compressor Blade in an Aero Gas Turbine Engine

  • R. K. Mishra
  • Johney Thomas
  • K. Srinivasan
  • Syed Iftekar Ahmed
Case History---Peer-Reviewed

Abstract

Failure of low-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 failed. The failure of the first stage rotor blade is found to be the first in the chain of events that led to the engine failure. The mode of failure in the blade is found to be fatigue and has originated from the mounting lug fillet region due to high stress concentrations. The failure has caused extensive damages in low-pressure compressor module and also in downstream modules as a secondary effect. Remedial measures are also suggested to prevent such failures.

Keywords

Failure analysis Fatigue failure Jet engine 

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Copyright information

© ASM International 2014

Authors and Affiliations

  • R. K. Mishra
    • 1
  • Johney Thomas
    • 2
  • K. Srinivasan
    • 2
  • Syed Iftekar Ahmed
    • 3
  1. 1.Regional Centre for Military Airworthiness (Engines)BangaloreIndia
  2. 2.Hindustan Aeronautics Limited - Engine DivisionBangaloreIndia
  3. 3.Aeronautical Quality Assurance (Engines)BangaloreIndia

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