Establishing probability of detection (POD) or reliability of various nondestructive testing (NDT) techniques is essential for implementing damage tolerant (DT) methodology for aero-engines. This POD is usually established with the help of a large number of service expired aero-engine components containing several fatigue cracks. In the absence of such components, artificial defects such as electrical discharge machining (EDM) notches or starter cracks were explored. However, such artificial defects would not meet the key features such as tightness of the fatigue cracks and the possible oxidation in the crack opening and thus, limiting their usage. Therefore, in the current study, an innovative approach of generating fatigue cracks at 650 °C (~ typical aero-engine service temperatures) with key high temperature service degradation aspects of oxidation and fatigue cracking is demonstrated for the first time using Gleeble^® test system. Further, POD is estimated by inspecting these laboratory generated fatigue cracks using fluorescent liquid penetrant technique (FLPT) and eddy current technique (ECT) under HIT (defect detected) vs. MISS (defect not detected) and â (signal response) vs. a (crack size) methodologies. The current study also discusses a statistical approach of random generation of crack sizes for use in NDT reliability analysis. In addition, an attempt has been made to understand the effect of a_90/95 values on remnant life calculations. It is concluded that the eddy current response of oxidized fatigue cracks results in better (high sensitive) a_90/95 values compared to the eddy current response obtained from non-oxidized fatigue cracks.

建立检测概率（POD）或各种无损检测（NDT）技术的可靠性对于实施航空发动机的容错（DT）方法至关重要。该POD通常是在大量已失效的航空发动机部件的帮助下建立的，该部件包含多个疲劳裂纹。在没有此类组件的情况下，已探究了人为缺陷，例如放电加工（EDM）缺口或起动器裂纹。但是，这样的人为缺陷将不能满足关键特征，例如疲劳裂纹的紧密性和裂纹开口处可能的氧化，从而限制了它们的使用。因此，在目前的研究中，^®测试系统。此外，在HIT（检测到缺陷）与MISS（未检测到缺陷）和â（信号响应）与a的比较下，通过使用荧光液体渗透剂技术（FLPT）和涡流技术（ECT）检查这些实验室产生的疲劳裂纹来估计POD。（裂缝大小）方法。当前的研究还讨论了用于NDT可靠性分析的随机生成裂纹尺寸的统计方法。另外，已尝试理解_90/95值对剩余寿命计算的影响。结论是，氧化疲劳裂纹的涡流响应可产生更好的（高灵敏度）_90/95 值与未氧化疲劳裂纹得到的涡流响应进行比较。