فناوری در مهندسی هوافضا

فناوری در مهندسی هوافضا

بررسی نقش توزیع ضریب انتقال حرارت جابه‌جایی در بهینه سازی مجاری خنک کاری داخلی تیغه توربین گاز

نوع مقاله : علمی پژوهشی

نویسندگان
1 دانشکده مهندسی مکانیک، دانشگاه صنعتی امیرکبیر، تهران، ایران
2 دانشکده مهندسی، دانشگاه اراک ، اراک، ایران
چکیده
در این مقاله، بازطراحی و بهینه‌سازی هندسه مجاری خنک‌کننده داخلی تیغه توربین گاز با هدف کاهش بیشینه دمای سطح تیغه انجام شده است. مدل سه‌بعدی جریان و انتقال حرارتِ کوپل‌شده در نرم‌افزار Star-CCM+ حل شده و برای کاهش هزینه محاسباتی، از ترکیب بهینه‌سازی تک‌متغیره و الگوریتم تاگوچی جهت تعیین تعداد، مکان و قطر سوراخ‌ها با رعایت قیود عدم تداخل و ثابت نگه‌داشتن دبی کل استفاده شده است. شرایط مرزی جریان گاز داغ و خنک‌کننده مطابق آزمایش‌های مرجع هیلتون و همکاران [24] انتخاب شده و عدد رینولدز متناظر با همان شرایط آزمایشگاهی تعریف می‌شود. شایان ذکر است که شرایط مرزی جریان خارجی مطابق داده‌های تجربی مرجع [24] تنظیم شد؛ به‌طوری‌که عدد ماخ ورودی در حدود 16/0 و عدد رینولدز ورودی در بازه(4/3–4/6)×10^5 به‌ترتیب بر مبنای وتر محوری و وتر حقیقی در مجموعه داده اعتبارسنجی در نظر گرفته شد. نتایج نشان داد با افزایش تعداد سوراخ‌ها از یک تا ده، بیشینه دمای سطح از 3/811 به 9/728 کلوین کاهش می‌یابد، اما نرخ کاهش پس از شش سوراخ به‌طور محسوسی کاهشی است. بر این اساس، پیکربندی شش ‌سوراخ با کاهش ۶۵ کلوینی نسبت به‌حالت پایه، یکنواختی حرارتی بالاتر و دبی متعادل‌تر به‌عنوان گزینه صنعتیِ پیشنهادی معرفی شد. همچنین نقشه ضریب انتقال حرارت جابه‌جایی خارجی روی سطح تیغه استخراج و با داده‌های تجربی اعتبارسنجی و از آن برای مکان‌یابی مؤثر سوراخ‌ها در نواحی با انتقال حرارت بالا استفاده شد
کلیدواژه‌ها
موضوعات

عنوان مقاله English

Investigation of the Role of Convective Heat Transfer Coefficient Distribution in the Optimization ot Internal Cooling Passages of a Gas Turbine Blade

نویسندگان English

Amin valizade pasha 1
seyyed salman Norazar 1
Hamed Safikhani 2
1 Faculty of Mechanical Engineering, Amirkabir University of Technology, Tehran, Iran
2 Department of Mechanical Engineering, Faculty of Engineering, Arak University, Arak, Iran
چکیده English

In this study, the geometry of internal cooling passages in a gas turbine blade is redesigned and optimized with the aim of reducing the maximum surface temperature. A three-dimensional coupled flow and heat-transfer model is solved in STAR-CCM+. To reduce computational cost, a hybrid approach combining single-variable optimization and the Taguchi method is used to determine the number, location, and diameter of the cooling holes, subject to non-interference constraints and a constant total coolant mass flow rate. The boundary conditions for the hot-gas and coolant streams are selected based on the experiments of Hilton et al. [24], and the Reynolds number is defined consistently with those laboratory conditions. Specifically, the external-flow boundary conditions are tuned to the experimental dataset in [24], with an inlet Mach number of approximately 0.16 and an inlet Reynolds number in the range (3.4–6.4) ×10^5, defined based on the axial chord and the true chord, respectively, in the validation dataset. The results show that increasing the number of holes from one to ten reduces the maximum surface temperature from 811.3 to 728.9K; however, the marginal temperature reduction decreases noticeably beyond six holes. Accordingly, a six-hole configuration is proposed as an industrially practical option, providing a 65 K reduction relative to the baseline case, improved thermal uniformity, and a more balanced coolant distribution. In addition, the external convective heat-transfer coefficient map over the blade surface is extracted and validated against experimental data, and then used to place holes more effectively in regions of high heat transfer

کلیدواژه‌ها English

Cooling channel geometry optimization
gas turbine blade
external convective heat transfer coefficient
Taguchi algorithm
convective heat transfer
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دوره 10، شماره 3
پاییز 1405
صفحه 1-16

  • تاریخ دریافت 29 بهمن 1404
  • تاریخ بازنگری 08 اسفند 1404
  • تاریخ پذیرش 22 اردیبهشت 1405
  • تاریخ اولین انتشار 16 خرداد 1405