نوع مقاله : مقاله پژوهشی
نویسندگان
1 دانشکده مهندسی مکانیک، دانشگاه سمنان، سمنان، ایران
2 گروه مهندسی مکانیک، دانشگاه صنعتی شریف، تهران، ایران
3 دانشکده مهندسی هوافضا، دانشگاه علوم و فنون هوایی شهید ستاری، تهران، ایران
کلیدواژهها
عنوان مقاله English
نویسندگان English
In this study, the performance of a thermal anti-icing system utilizing hot air extracted from the engine compressor is analytically investigated to prevent ice accretion on the leading edge of the engine air intake. The calculations are performed for critical icing conditions, including an altitude of 3000 meters, a flight Mach number of 0.45, and an ambient temperature of −30°C. By simultaneously solving the energy balance equations for the hot-air heating channel (with an inlet temperature of 200°C) and the external surface of the leading edge, the surface temperature distribution as well as the internal and external convective heat transfer coefficients are determined at four different clock positions (12, 9, 6, and 3 o'clock). The results indicate that with appropriate design of the heating channels, the surface temperature remains above the freezing point at all locations. Furthermore, increasing the number of heating channels and the hot-air mass flow rate ratio directly enhances the surface temperature and improves the overall system performance. The proposed analytical model can serve as a fast and efficient tool for the preliminary design of anti-icing systems.
کلیدواژهها English
