面向适航要求的涡轮发动机限寿件概率失效风险评估方法  

Probabilistic failure risk assessment method of turbine engine life limited parts for airworthiness requirements

作　　者：张弓[1,2] 周燕佩[1,2] 丁水汀[3] 

机构地区：[1]中国民用航空局中国民用航空发动机适航审定中心,北京100102 [2]中国民航科学技术研究院发动机适航审定中心筹建办公室,北京100028 [3]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2015年第10期2338-2345,共8页Journal of Aerospace Power

摘　　要：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 requirement of airworthiness regulations on engine life limited parts （ELLPs）, a theoretical model integrating stress-strength interference model, linear elastic fracture mechanics and zone based probabilistic analysis was established to as- sess the failure risk of ELLPs. The numerical algorithm and the computer program were also developed. The method was calibrated by the test case provided in the advisory circular. The assessment results are 1.45 × 10^-9 times/cycle without any non-destructive inspection and 1.0×10 ^-9 times/cycle with an inspection at 10000 cycles, respectively. The results measure up to the calibration test case very well, indicating the method to meet the terms of the regu- lation, thus is applicable to the current civil engine type certification.

关 键 词：适航 涡轮发动机 发动机限寿件 失效风险 概率风险评估 

分 类 号：V232.3[航空宇航科学与技术—航空宇航推进理论与工程]