Modeling and studying a gas turbine blade under mechanical and thermal loads
محل انتشار: پنجمین کنفرانس ملی مهندسی مکانیک و هوافضا
سال انتشار: 1399
نوع سند: مقاله کنفرانسی
زبان: انگلیسی
مشاهده: 751
فایل این مقاله در 6 صفحه با فرمت PDF قابل دریافت می باشد
- صدور گواهی نمایه سازی
- من نویسنده این مقاله هستم
استخراج به نرم افزارهای پژوهشی:
شناسه ملی سند علمی:
MECHAERO05_049
تاریخ نمایه سازی: 27 مرداد 1399
چکیده مقاله:
One of the key elements in airplane’s jet engine is the blades of gas turbine, accordingly modeling and analyzing them can be beneficial. Pressure distribution on external surface and inertia force of rotation leads to three-dimensional distribution on turbine’s blades. Engines works in high temperature situations and since a large amount of air are suckedin high velocity, they face various damages which causes failure indifferent sections. In general, engines are comprised of four parts, which are fan, compressor, combustion chamber and turbine. Turbine is at the bottom of the engine and high temperature are passes through it while experiencing different loads. The method to study the stress distribution of the blade and its holder disk is finite element, which the Abaqus software is used in this paper
کلیدواژه ها:
نویسندگان
Fatemeh Gheytasvand
Department of Mechanical Engineering, Faculty of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran
Zahra Abdoli
Department of Mechanical Engineering, Faculty of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran
Ehsan Anbarzadeh
Department of Mechanical Engineering, Faculty of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran