Abstract
Failed stator vanes of various aero-engines were subjected to investigations. Stator segment designated as SV-1 failed due to impact by large iron containing object generated possibly inside the turbine. Damage on the vanes of stator segment termed as SV-2 has taken place by stress rupture at low stress and high temperature. Stator segment of another aero-engine termed as SV-3 is degraded by impact abrasion of iron containing particles. Investigation reveals that thermo-mechanical fatigue is responsible for large crack generation of stator vanes obtained from another aero-engine referred as SV-4. In contrast, multiple small cracks are formed because of creep fatigue interaction also known as thermal fatigue for impairment of another segment of the same aero-engine denoted as SV-5. Finally, measures to be taken for improving service life of these stator segments are discussed.
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