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某型航空发动机在外场服役过程中出现声音异常现象,地面检查发现高压1,2级涡轮叶片以及高压2级涡轮导向叶片全部折断。通过现场勘查、断口分析以及金相检查等手段,确认了由伸根梨形孔处断裂的高压1级涡轮叶片是该次失效的首断件,聚集分布的铸造疏松缺陷是引起其早期疲劳断裂的主要原因;其他各级涡轮叶片断裂均属二次损伤引起的过载断裂。
A certain type of aero-engine appeared abnormal sound during service in the field. The ground inspection revealed that the high-pressure 1,2-stage turbine blades and the high-pressure 2-stage turbine guide blades were all broken. Through site investigation, fracture analysis and metallographic examination, it was confirmed that the first-stage high-pressure turbine blade ruptured from the root-shaped pear-shaped hole was the first failure of this failure. The loosely distributed casting defects caused the early fatigue fracture The main reason; other levels of turbine blade fracture are secondary damage caused by overload fracture.