A numerical investigation of film cooling operating parameters on a two-dimensional turbine blade
محل انتشار: هجدهمین کنفرانس انجمن هوافضای ایران
سال انتشار: 1398
نوع سند: مقاله کنفرانسی
زبان: انگلیسی
مشاهده: 360
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شناسه ملی سند علمی:
AEROSPACE18_138
تاریخ نمایه سازی: 31 اردیبهشت 1399
چکیده مقاله:
The present work consists of film cooling analysis on a flat plate and a pre -designed turbine blade with film cooling holes. The effect of three parameters: film cooling velocity, temperature, and main flow velocity were investigated. In the end, it was illustrated that with the increase of film cooling velocity the temperature of the blade wall decreases and also, as it may be obvious, the temperature of the blade wall decreases as the temperature of film cooling decreases. But the important point here was that it was linearly effective on the temperature of the wall. In addition, the effect of main flow velocity was not that much as it was being changed by the change of pressure difference at the outlet and inlet of the domain.
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نویسندگان
M.R. Negahban A.
Graduate student, Aerospace Department, Sharif University of Technology, Azadi St., Tehran, Iran
Ali Madadi
Assistant professor, Aerospace Department, Amirkabir University of Technology, Hafez ave., Tehran, Iran