نوع مقاله : علمی- ترویجی

نویسندگان

1 عضو هیئت علمی دانشکده فنی مهندسی ، دانشگاه آزاد اسلامی واحد چالوس، چالوس، ایران

2 دانشجو دانشگاه آزاد اسلامی ، واحد آیت اله آملی

3 کارشناس ارشد، دانشگاه آزاد اسلامی ، واحد فیروزکوه، تهران، ایران

چکیده

در طراحی موتور سوخت مایع به‌دلیل دمای بالای احتراق و نرخ بالای انتقال از گازهای داغ به دیوار محفظه، خنک‌کاری محفظة رانش اهمیت بسیار بالایی دارد. در طراحی خنک‌کاری محفظة رانش، انتخاب روش مناسب، طراحی مجاری خنک‌کاری و مباحث مرتبط با محفظة رانش دو جداره و استفاده از پوشش‌های حرارتی  اهمیت بسیار زیادی دارد. در دیوارة محفظة احتراق و نازل موتور پیشران مایع لازم است یک سیستم خنک‌کاری به‌منظور جلوگیری از شکست مقاومت بدنة موتور استفاده شود. در خنک‌کاری به روش بازیابی سیال مبرد (معمولاً سوخت) از میان کانال‌هایی که برای آن در بدنة موتور تعبیه شده است، عبور می‌کند و دمای بدنة موتور را کاهش می‌دهد. مدل‌سازی و تحلیل جریان سیال کانال خنک‌کننده در موتور پیشران مایع به‌دلیل شار حرارتی بالا یکی از مهم‌ترین و چالشی‌ترین موضوع در زمینة این نوع موتورهاست. در این مقاله، فرایند احتراق با استفاده از روش دینامیک سیالات محاسباتی مورد بررسی قرار گرفت. برای این کار ابتدا مطالعة روی کارهای مشابه منتشر شده در این زمینه انجام شد. سپس، معادلات موجود و لازم برای شبیه‌سازی این فرایند استخراج شد. در نهایت با استفاده از روش عددی انتخاب شده برای حل احتراق، شبیه‌سازی برای هندسة موجود در دبی‌های مختلف انجام شد که نتایج قابل قبولی دارد.

کلیدواژه‌ها

عنوان مقاله [English]

Analysis of the Combustion Process in the Engine Zamstic

نویسندگان [English]

  • Koros nekofar 1
  • Andisheh Tiregar 2
  • seyed Amir Hosseini 3

1 Member of the Faculty of Technical Engineering, Islamic Azad University, Chalus Branch, Chalus, Iran

2 Student of Islamic Azad University, Ayatollah Amoli branch

3 Master's degree, Islamic Azad University, Firuzkoh Branch, Tehran, Iran

چکیده [English]

In liquid rocket engine design, because of the combustion due to the high temperatures and high rates of heat transfer (1MW/m2 to about 160MW/m2) of hot gases to the chamber walls, the cooling thrust
chamber is of utmost importance. Also, the thrust chamber cooling design, the selection of appropriate methods, as well as the design and topics related to thrust chamber cooling ducts, double glazing and thermal coating are very important. Liquid propellant engine in the wall of the combustion chamber and nozzle is a necessary part in order to prevent the failure of a cooling system using engine block
resistance. In this paper, the combustion process is investigated using a computational fluid dynamics method. To do this, first the similar works in the field are reviewed and then the equations that exist for this process are extracted to determine what equations need to be solved. By examining this method, it was determined that the chosen numerical method could be used to solve the combustion equation. Finally, the simulation results for the geometry in different fluxes are studied which led to acceptable outcomes.

کلیدواژه‌ها [English]

  • Liquid Propellant Engine
  • The Combustion Chamber
  • Cooling Channel
  • Cryogenic Fuels
  • Regenerative Cooling
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