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.

对各种航空发动机的故障定子叶片进行了调查。定子段指定为SV-1失败，原因是可能在涡轮机内部产生的含铁大物体撞击。在低应力和高温下的应力破裂已使定子段的叶片损坏，称为SV-2。另一架称为SV-3的航空发动机的定子部分会因含铁颗粒的撞击磨损而退化。调查表明，热机械疲劳是导致从另一架航空发动机SV-4获得的定子叶片大裂纹产生的原因。相反，由于蠕变疲劳相互作用（也称为热疲劳）而形成多个小裂纹，以破坏同一航空发动机的另一部分，称为SV-5。最后，