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نویسندگان مقالات پربازدید :
تجزیه و تحلیل شکست مهندسی
جزئیات رویداد
اینستاگرام تی پی بین
همایش ، رویداد ، ژورنال
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  • creep failure of low pressure turbine blade of an aircraft engine

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    • تاریخ ارائه: 1390/01/01
    • تاریخ انتشار در تی پی بین: 1390/01/01
    • تعداد بازدید: 711
    • تعداد پرسش و پاسخ ها: 0
    • شماره تماس دبیرخانه رویداد: -
      a low pressure turbine blade of an aircraft engine was fractured during the ground test run. the failed as well as neighboring unfailed blades were studied during failure investigation. microstructure of a virgin blade was also analyzed for reference. the material of the blade was udimet 500, a high strength ni-base super alloy. the investigation revealed that the triple point creep cracks were initiated on the trailing edge of blade-airfoil near root region. grain dropping was also observed within these cracks. one of these cracks was propagated under the high cycle fatigue mechanism, circumscribing almost 50% of the fracture area. when this fatigue crack might have propagated to a critical length, the airfoil of the blade fractured catastrophically under overload condition. the primary cracking was due to creep. such cracks were also present on the same location of neighboring blades indicating that they were also prone to failure.

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