Compliance verification method for pressurized engine static parts of aircraft engine airworthiness
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摘要: 对《航空发动机适航规定》(CCAR33-R2)新增条款CCAR33.64(静承压件)进行解读与分析,结合试验设计法、数值模拟法开展针对航空发动机静承压件适航条款的符合性验证方法和验证流程的研究.提出针对CCAR33.64的符合性验证流程,并以某型航空发动机低压涡轮后机匣的模型为例进行验证.选取机匣的最大工作压力和1.1倍最大工作压力分别作为加载条件进行数值模拟,得出最大等效应力分别为453MPa和534MPa,最大机匣变形分别为0.366mm和0.432mm,不会出现永久变形或机匣破裂的情况,满足适航要求.验证了该流程的适航符合性,为制定航空发动机静承压件适航指南提供参考依据.Abstract: The newly added airworthiness terms of CCAR33.64 (pressurized engine static parts) in "aircraft engine airworthiness regulations"(CCAR33-R2) was studied and analyzed. Experiment design method and numerical simulation method were utilized in the process to do research on pressurized engine static parts with compliance verification method and verification flow. Compliance verification process for CCAR33.64 was founded and the example of a certain type of low pressure turbine back rear casing for aircraft engine was performed. The maximum working pressure and 1.1 times maximum working pressure were taken in numerical simulation to analysis. Maximum equivalent stress were 453MPa and 534MPa. Maximum deformation were 0.366mm and 0.432mm. No permanent deformation or rupture of casing proves its compliance which provides reference for establishing airworthiness guide for pressurized engine static parts of aircraft engines.
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