تخمین عمر خزشی خستگی پره توربین گازی فشار بالا با درنظر گرفتن اندرکنش سیال سازه

نوع مقاله : مقاله پژوهشی

نویسندگان

دانشکده مهندسی مکانیک، دانشگاه خواجه نصیرالدین طوسی، تهران، ایران

چکیده

برای مطالعه عمر خزش-خستگی کم‌چرخه چندمحوره در پره‌های توربین فشار بالا، یک مدل پیش‌بینی عمر خستگی کم‌چرخه چندمحوره بر اساس یک پارامتر جدید آسیب صفحه بحرانی در این پژوهش ارائه شده است. ابتدا، با انجام تحلیل کوپل حرارتی-سازه‌ای سه‌بعدی پره‌های توربین فشار بالا، توزیع تنش و کرنش تحت بارگذاری‌های مختلف شامل نیروی گریز از مرکز، بارگذاری حرارتی و بارگذاری آیرودینامیکی به دست آمد. سپس، مدل پیش‌بینی عمر خستگی کم‌چرخه چندمحوره و معادله لارسون میلر برای پیش‌بینی عمر خستگی و عمر خزشی پره به‌طور جداگانه به کار گرفته شدند. علاوه بر این، برای بررسی مکانیزم آسیب خستگی در اندرکنش خزش-خستگی تحت شرایط دما بالا، از روش‌های تجربی موجود در مطالعات پیشین استفاده شد و مدل پیش‌بینی عمر اندرکنش خزش-خستگی نیز به طور همزمان توسعه یافت. در ادامه، نتایج پیش‌بینی عمر خزش-خستگی نشان داد عمر پره توربین گازی با در نظر گرفتن اندرکنش خزش-خستگی نسبت به حالتی که اندرکنش لحاظ نشده است به میزان 43.7 % درصد کاسته شده است. در نهایت، نتایج آشکار ساخت مدل پیش‌بینی عمر خستگی کم‌چرخه چندمحوره منطقی بوده و اندرکنش خزش-خستگی نباید نادیده گرفته شود.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Predicting the Creep–Fatigue life of a high-pressure gas turbine blade considering Fluid–Structure interaction

نویسندگان [English]

  • Ali Zolfaghari
  • Amir Reza Shahani
  • Narges Asadpour
Department of Solid Mechanics, Faculty of Mechanical Engineering, K. N. Toosi University of Technology, Tehran, Iran
چکیده [English]

To study the multiaxial low-cycle creep-fatigue life of high-pressure turbine blades, a multiaxial low-cycle fatigue life prediction model based on a new critical plate damage parameter is presented in this paper. First, by performing a three-dimensional thermal-structural coupling analysis of high-pressure turbine blades, the stress and strain distributions under different loadings including centrifugal force, thermal loading, and aerodynamic loading were obtained. Then, the multiaxial low-cycle fatigue life prediction model and the Larson-Miller equation were applied to predict the fatigue life and creep life of the blade separately. In addition, to investigate the fatigue damage mechanism in creep-fatigue interaction under high temperature conditions, the experimental methods available in previous studies were applied, and the creep-fatigue interaction life prediction model was also developed simultaneously Furthermore, the results of creep-fatigue life prediction indicated that in case of considering the creep-fatigue interaction, the life of the gas turbine blade was reduced by 43.7% , compared to the case where the interaction was not considered. Also, the maximum fatigue damage was concentrated at point A and the maximum creep damage was concentrated at point B. Finally, the results revealed that the multiaxial low-cycle fatigue life prediction model was reasonable and the creep-fatigue interaction should not be ignored.

کلیدواژه‌ها [English]

  • High Pressure Gas Turbine Blade
  • Creep Fatigue
  • Fluid–Structure Interaction
  • Conjugate Heat Transfer
  • CFD and FEM Simulations
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