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طراحی و بهینهسازی آیرودینامیکی کمپرسور 10 مرحله‌‌‌‌ای و فن 3 مرحله‌‌‌‌ای یک موتور توربوفن با نسبت کنارگذر کم | ||
| مکانیک سیالات و آیرودینامیک | ||
| مقاله 10، دوره 13، شماره 1 - شماره پیاپی 33، مرداد 1403، صفحه 131-147 اصل مقاله (1.94 M) | ||
| نوع مقاله: مقاله پژوهشی | ||
| نویسندگان | ||
| مصطفی محمودی* 1؛ جاماسب پیرکندی2؛ مهدی جهرمی3 | ||
| 1دانشیار، دانشگاه صنعتی مالک اشتر،تهران،ایران | ||
| 2دانشیار، دانشگاه صنعتی مالک اشتر،تهران، ایران | ||
| 3استادیار، دانشگاه صنعتی مالک اشتر،تهران،ایران | ||
| تاریخ دریافت: 16 اردیبهشت 1403، تاریخ بازنگری: 18 خرداد 1403، تاریخ پذیرش: 16 تیر 1403 | ||
| چکیده | ||
| در این مطالعه، بخش تراکم یک موتور توربوفن با نسبت کنارگذر کم طراحی و بهینه شده‌است. این موتور از یک فن محوری سه مرحله‌‌‌‌ای و یک کمپرسور محوری ده مرحله‌‌‌‌ای برای تراکم بهره می‌برد. در این مطالعه، ابتدا با یک نرم افزار تجاری و بر اساس نتایج تحلیل چرخه موتور، طراحی مقدماتی قسمت تراکم موتور به انجام رسیده، سپس عملکرد طرح، با استفاده از دینامیک سیالات محاسباتی مدل‌سازی شده‌است. این چنین، عملکرد طرح ارائه‌‌‌‌‌شده توسط نرم افزار ارزیابی شده و درصد انحراف آن از مطلوب تحلیل سیکل محاسبه شده‌است. به کمک تحقیقات قبلی، سپس طرح اولیه بهینه گشته تا با کاهش انحرافات عملکردی، دبی و نسبت فشار مورد نظر به دست آید. نتایج نشان می‌دهد که نرم‌افزار تجاری قادر به تولید طرح‌هایی در حاشیه ۲۰ تا ۳۰ درصدی نقطه طراحی مورد نظر است. همچنین می‌توان خطای طراحی را از طریق بهینهسازی به کمتر از 20 درصد کاهش داد. در طول بهینهسازی، دبی جرمی‌فن از 74 به 86 کیلوگرم بر ثانیه افزایش یافت، در حالی که دبی کمپرسور از 57 به 59 کیلوگرم بر ثانیه افزایش داشته‌است. نسبت فشار فن نیز از 46/2 به 54/2 و نسبت فشار کمپرسور از 24/5 به 34/6 افزایش یافته‌است. این مطالعه با بهینهسازی بر اساس یافته های قبلی، توانست راندمان فن را 7/0 درصد و راندمان کمپرسور را 5/1 درصد افزایش دهد. کاهش قدرت امواج ضربه‌‌‌‌ای در محفظه فن و کمپرسور موجب چنین افزایشی شده‌است. | ||
| کلیدواژه‌ها | ||
| کمپرسور محوری؛ فن محوری؛ موتور توربوفن؛ بهینهسازی آیرودینامیکی | ||
| عنوان مقاله [English] | ||
| Aerodynamic design and optimization of a 10 stage compressor and a 3 stage fan of a low bypass ratio turbofan engine | ||
| نویسندگان [English] | ||
| Mostafa Mahmoodi1؛ Jamasb Pirkandi2؛ Mehdi Jahromi,3 | ||
| 1Associate Professor, Malek Ashtar University of Technology, Tehran, Iran | ||
| 2Associate Professor, Malek Ashtar University of Technology, Tehran, Iran | ||
| 3Assistant Professor, Malek Ashtar University of Technology, Tehran, Iran | ||
| چکیده [English] | ||
| This research focuses on the design and optimization of the compression section of a low bypass ratio turbofan engine. The engine employs a three-stage axial fan and a ten-stage axial compressor for compression. Initially, a commercial software was used to conduct a preliminary design of the engine’s compression section based on engine cycle analysis results. The design’s performance was then modeled using computational fluid dynamics. This allowed for the evaluation of the software’s design performance and the calculation of its deviation percentage from the desired cycle analysis. Subsequently, insights from previous studies were utilized to optimize the initial design. The goal was to achieve the desired flow rate and pressure ratio by minimizing performance deviations. The findings indicate that the commercial software can generate designs that are within 20-30% of the desired design point. Moreover, it is feasible to reduce the design error to less than 20% through optimization. During the optimization process, the fan’s flow rate increased from 74 to 86 kg/s, while the compressor’s flow rate rose from 57 to 59 kg/s. The pressure ratio of the fan also increased from 2.46 to 2.54, and the compressor’s pressure ratio rose from 5.24 to 6.34. By leveraging previous research for optimization, the study managed to enhance the fan’s efficiency by 0.7% and the compressor’s efficiency by 1.5%. This increase was attributed to the reduction in shock waves in the fan and compressor chamber. | ||
| کلیدواژه‌ها [English] | ||
| axial compressor, axial fan, turbofan engine, aerodynamic optimization | ||
| مراجع | ||
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آمار تعداد مشاهده مقاله: 258 تعداد دریافت فایل اصل مقاله: 24 |
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