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Significant Factors

Summary

  1. Onset of the engine non-synchronous vibration excited reverse bending of the first-stage compressor blisk blade in the second or higher bending modes.
  2. Presence of fatigue cracking in the mid-span location on a single first-stage compressor blisk blade led to blade separation.
  3. Damage to the downstream engine components by the separated portion of the blade resulted in a loss of engine power and increased inter-stage turbine temperature.
 
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