航空发动机典型任务剖面归纳方法

A Study of Inductive Method of Typical Mission Profiles of Aero-engine

航空发动机典型任务剖面不仅需要反映飞行任务特点,而且需要衡量飞行任务对发动机寿命损伤大小。将发动机低周疲劳损伤、稳态蠕变损伤、热冲击损伤作为任务剖面归纳的主导因素。针对某型发动机确定了13个飞行参数共77个统计量作为任务剖面归纳的原始载荷矩阵,用系统聚类法、主成分聚类法、模糊聚类法对71个飞行剖面进行了聚类归纳。对比分析表明:确定的任务剖面原始载荷矩阵充分代表了发动机使用用法,参数彼此具有较强的独立性;相比其他2种聚类法,系统聚类法归纳的任务剖面集合能够充分反映该类任务剖面的共同特点和属性。

Typical mission profiles of aero-engine not only represent flight mission characteristics, but also weigh up life damage resulting from flight missions. Low cycle fatigue damage, steady creep damage and thermal shock damage are regarded as the dominate elements of mission profile induction. In view of a cer- tain type of aero-engine 77 statistical parameters of 13 flight parameters are composed of original load ma- trix, and then 71 flight profiles are clustered and induced on the system clustering method, principal com- ponent clustering method and fuzzy clustering method. The results show that the original load matrix re- flects aero-engine usage employ and that parameters of profile induction have strong independence from each other. In comparison with other methods, the method enable to reflect corporate characteristics and mission profile collections on the system clustering attributes.