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Seddik Bouchouicha, Malika, Boualem, Khadidja, Ben Ali Kouchih, Fatima, SOUSSA, Abdelhalim, AZZI, Abbès. (1404). NUMERICAL STUDY OF A NOVEL DIVERGING-EXIT HOLE FOR IMPROVED FILM COOLING PERFORMANCE. نشریه هنرهای کاربردی, (), -. doi: 10.22075/jhmtr.2025.38591.1800
Malika Seddik Bouchouicha; Khadidja Boualem; Fatima Ben Ali Kouchih; Abdelhalim SOUSSA; Abbès AZZI. "NUMERICAL STUDY OF A NOVEL DIVERGING-EXIT HOLE FOR IMPROVED FILM COOLING PERFORMANCE". نشریه هنرهای کاربردی, , , 1404, -. doi: 10.22075/jhmtr.2025.38591.1800
Seddik Bouchouicha, Malika, Boualem, Khadidja, Ben Ali Kouchih, Fatima, SOUSSA, Abdelhalim, AZZI, Abbès. (1404). 'NUMERICAL STUDY OF A NOVEL DIVERGING-EXIT HOLE FOR IMPROVED FILM COOLING PERFORMANCE', نشریه هنرهای کاربردی, (), pp. -. doi: 10.22075/jhmtr.2025.38591.1800
Seddik Bouchouicha, Malika, Boualem, Khadidja, Ben Ali Kouchih, Fatima, SOUSSA, Abdelhalim, AZZI, Abbès. NUMERICAL STUDY OF A NOVEL DIVERGING-EXIT HOLE FOR IMPROVED FILM COOLING PERFORMANCE. نشریه هنرهای کاربردی, 1404; (): -. doi: 10.22075/jhmtr.2025.38591.1800

NUMERICAL STUDY OF A NOVEL DIVERGING-EXIT HOLE FOR IMPROVED FILM COOLING PERFORMANCE

Journal of Heat and Mass Transfer Research
مقالات آماده انتشار، پذیرفته شده، انتشار آنلاین از تاریخ 08 آذر 1404
نوع مقاله: Full Length Research Article
شناسه دیجیتال (DOI): 10.22075/jhmtr.2025.38591.1800
نویسندگان
Malika Seddik Bouchouicha؛ Khadidja Boualem؛ Fatima Ben Ali Kouchih؛ Abdelhalim SOUSSA* ؛ Abbès AZZI
Aero Hydrodynamic Naval Laboratory, (LAHN) USTO-MB, Oran, Algeria University of Science and Technology of Oran, MOHAMED BOUDIAF Faculty of Mechanical Engineering, BP1505 El-MNAOUAR, 31000, Oran, Algeria
تاریخ دریافت: 17 مرداد 1404،  تاریخ بازنگری: 19 آبان 1404،  تاریخ پذیرش: 08 آذر 1404 
چکیده
This study numerically investigates a series of novel lip-shaped divergent-exit hole configurations designed to enhance film cooling effectiveness on turbine blade surfaces. Six configurations were analyzed Full Lip (FL), Oval Lip (OL), Oval Upper Lip (OUL), Oval Lower Lip (OLL), Full Upper Lip (FUL), and Full Lower Lip (FLL) using Reynolds-Averaged Navier–Stokes (RANS) simulations with the RNG k–ε turbulence model. The computational results were validated against experimental data for a baseline cylindrical hole at multiple blowing ratios (M = 0.5, 1.0, and 1.5). The findings indicate that all lip-shaped geometries improved the laterally averaged film cooling effectiveness compared with the conventional cylindrical hole, with the FL configuration exhibiting the most consistent performance. At M = 1.5, the FL hole achieved up to 100% enhancement in film cooling effectiveness relative to the baseline, primarily due to improved coolant attachment and suppression of jet lift-off. These results demonstrate the potential of asymmetric lip-shaped exits to achieve more uniform cooling coverage and higher thermal protection under realistic turbine operating conditions.
کلیدواژه‌ها
Film cooling؛ hole geometry؛ shaped holes؛ cooling effectiveness؛ blowing ratio
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تعداد مشاهده مقاله: 9


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