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为了满足适航规章关于民用航空涡轮发动机限寿件的要求,通过综合分区概率统计、应力-强度干涉理论、线弹性断裂力学等方法建立了限寿件失效的概率风险评估数学模型,确定了模型的数值解法,开发了计算程序,并结合咨询通告中所提供的校准算例完成了模型的验证工作.评估结果表明,寿命期内不进行无损探伤检查和在10 000循环进行一次检查的限寿件示例失效风险分别为1.45×10-9次/飞行循环和1.0×10-9次/飞行循环,完全符合校准算例,表明了评估方法能够反映适航规章关于限寿件失效风险分析的要求.
In order to meet the requirements of airworthiness regulation on civil aviation turbine engine life-limited parts, a mathematic model of probabilistic risk assessment of life-limited parts failure was established by means of integrated zoning probability statistics, stress-strength interference theory and linear elastic fracture mechanics. The model , The numerical program has been developed and the calculation procedure has been developed and the verification of the model has been completed in conjunction with the calibration examples provided in the advisory circular.The results of the assessment indicate that no life-cycle flaw detection and non-destructive testing at 10 000 cycles The example failure risk is 1.45 × 10-9 cycles / flight cycle and 1.0 × 10-9 cycles / flight cycle, respectively, in full compliance with the calibration example, indicating that the assessment method is capable of reflecting the requirements of the airworthiness regulations regarding failure risk analysis of limit-set pieces .