تحقیقات موتور

تحقیقات موتور

طراحی مفهومی محفظة احتراق توربین گاز هوایی متعارف به منظور کاهش دوده و آلاینده‌های گازی

نوع مقاله : مقاله پژوهشی

نویسندگان
1 دانشکده مهندسی مکانیک، دانشگاه تربیت مدرس، تهران، ایران
2 پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
3 دانشکده مهندسی مکانیک، دانشگاه علم و صنعت ایران، تهران، ایران
4 شرکت منشاء طراحی هوشمند پیشرو، شیراز، ایران
چکیده
در این پژوهش، یک روش نوین برای طراحی مفهومی محفظة احتراق توربین گازی هوایی با هدف کاهش دوده و آلاینده‌های گازی ارائه شده است. این روش مبتنی بر استفاده از الگو‌های شبکه واکنشگرهای شیمیایی (CRN) و شبیه‌‏سازی دقیق فرآیند احتراق جهت تحلیل چگونگی تشکیل و اکسیدشدن دوده در شرایط مختلف عملکردی موتور است. ابتدا با تعیین ابعاد اولیه محفظة احتراق، تحلیل جریان و واکنش‌های شیمیایی انجام شده و سپس مقدار آلاینده‌ها در سناریوهای مختلف عملیاتی مورد ارزیابی قرار گرفته است. نتایج حاصل نشان می‌دهد که الگوی پیشنهادی توانایی قابل توجهی در کاهش دوده و آلاینده‌های گازی نظیر NOx و CO داشته و در عین حال عملکرد ترمودینامیکی احتراق را نیز حفظ می‌کند. به طور خاص، مقایسه شاخص جرم ذرات غیرفرار (nvPM) مرجع ایکائو و مقدار پیش‌بینی‌شده در چرخة برخاست بترتیب 70.8 میلی‌گرم بر کیلوگرم و 73.7 میلی‌گرم بر کیلوگرم بوده است (اختلاف 4.1 درصد). همچنین، شاخص تعداد ذرات نیز بترتیب 4.02×1014و 4.16×1014 عدد بر کیلوگرم گزارش شده است (اختلاف 3.4 درصد). در تمامی چرخه‌های عملیاتی، اختلاف بین مقادیر پیش‌بینی‌شده و مرجع ایکائو در محدوده 3.4 درصد تا 4.4 درصد قرار دارد. این رویکرد می‌تواند به‌عنوان ابزاری مؤثر در طراحی‌های آینده محفظه‌های احتراق به‌منظور بهینه‌سازی بازده و کاهش اثرات زیست‌محیطی سامانه‌های پیشرانه هوایی مورد بهره‌برداری قرار گیرد.
کلیدواژه‌ها

عنوان مقاله English

Conceptual design of a conventional aero gas turbine combustor for soot and gaseous emissions reduction

نویسندگان English

Sajad Davari 1
Fathollah ommi 1
Zoheir Saboohi 2
Seyed Ehsan Hosseini 3 4
1 Mechanical Engineering Department Tarbiat Modares University, Tehran, Iran
2 Aerospace Research Institute, Ministry of Science, Research and Technology of Iran, Tehran, Iran
3 Department of Mechanical Engineering, Iran University of Science and Technology, Tehran, Iran
4 Pioneer Intelligence Design Origin Incorporation, Shiraz, Iran
چکیده English

In this research, a novel approach for the conceptual design of an aero gas turbine combustor aimed at reducing soot and gaseous emissions is presented. This method is based on the use of Chemical Reactor Network (CRN) models and detailed combustion process modeling to analyze how soot forms and oxidizes under various engine operating conditions. Initially, the primary dimensions of the combustor were determined, and flow and chemical reaction analyses were performed. Subsequently, the levels of pollutants were evaluated in different operational scenarios. The results show that the proposed model has a significant capability in reducing soot and gaseous pollutants such as NOx and CO, while also maintaining the thermodynamic performance of combustion. Specifically, the comparison of the ICAO reference non-volatile Particulate Matter (nvPM) mass emission index and the predicted value in the take-off cycle were 70.8 mg/kg and 73.7 mg/kg, respectively (a 4.1% difference). Also, the particle number emission index was 4.02×10¹⁴ #/kg and 4.16×10¹⁴ #/kg, respectively (a 3.4% difference). Across all operational cycles, the difference between the predicted values and the ICAO reference values is within the range of 3.4% to 4.4%. This approach can be utilized as an effective tool in the future design of combustors to optimize efficiency and reduce the environmental impacts of aerial propulsion systems.

کلیدواژه‌ها English

Conceptual Design
Combustor
Soot
Gaseous Emissions
Aero Gas Turbine
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