مدلسازی سه بعدی فرایند احتراق در یک موتور اسکرمجت با لحاظ کردن مکانیزم شیمیایی چند واکنشی

نوع مقاله : مقاله پژوهشی

نویسندگان

عضو هیات علمی / دانشگاه صنعتی مالک اشتر

چکیده

د
در این مقاله، فرایند احتراق در یک موتور اسکرم ­جت DLR با لحاظ­کردن مکانیزم شیمیایی چندواکنشی        مدل­سازی و تحلیل شده است. تحلیل انجام ­شده به­ کمک نرم ­افزار فلوئنت و به­ صورت دوبعدی و سه ­بعدی انجام شده است. نتایج تحقیق نشان می‌دهد که عملکرد کلی موتور اسکرم­جت در حالت سه ­بعدی شبیه به حالت دوبعدی است. مقدار نیروی پیش­رانش و بازده احتراق در شبیه‌سازی سه­بعدی به­ترتیب 0.9% و 1.4% با حل دوبعدی تفاوت دارد. به­ منظور درنظرگرفتن اثر تعداد واکنش­ها بر روی فرایند احتراق، احتراق هیدروژن به­ صورت دوبعدی با 19 زیرواکنش نیز شبیه ­سازی شده­ است. نتایج حل نشان می­ دهند که عملکرد کلی اسکرم­ جت در حالت ت ک­واکنشی و چندواکنشی مشابه است. بررسی­ ها نشان می ­دهد نیروی پیش­رانش و بازده احتراق در حالت چندواکنشی به ­ترتیب 4/1% و 4/4% با حالت تک ­واکنشی فرق دارند. در نقاطه مقابل، ناحیه فروصوت در حالت سه­ بعدی و چندواکنشی به ­ترتیب 48.9 و 17.7 درصد بیشتر از حالت پایه امتداد پیدا کرده است.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Three-dimensional modeling of the combustion process of a scramjet by considering multi-stage reaction mechanism

نویسندگان [English]

  • jamasb pirkandi
  • Mostafa Mahmoodi
Department of Aerospace Engineering, Maleke ashtar University
چکیده [English]

In this investigation, the combustion process in DLR scramjet is simulated and studied by considering multi-stage reaction mechanism. This study is conducted both three-dimensionally and two-dimensionally with the help of Fluent. The results indicate that the general performance of the scramjet is nearly the same for both the two-dimensional and three-dimensional cases, that is to say the difference between calculated thrust and combustion efficiency in these two cases is only 0.9% and 1.4%, respectively. To consider the effect of the chemical mechanism on the obtained results, a two-dimensional simulation of the scramjet is done with a detailed chemical mechanism, which includes 19 reactions. The results illustrate that the general performance of the scramjet is nearly the same. More accurately, the difference between thrust and combustion efficiency in the one-reaction and the multi-reaction cases is only 1.4% and 4.4%, respectively. In contrast, the subsonic region behind the strut in three-dimensional case and multi-stage reaction mechanism case are 48.9% and 17.7% longer than the base case, respectively.

کلیدواژه‌ها [English]

  • Supersonic combustion
  • Scramjet
  • numerical simulation
  • Turbulent Flow
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