بررسی تأثیر قطر پاشش بر مشخصات حوزه جریان پاشش متقاطع در جریان هوای عبوری فراصوت

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشجوی دکتری / دانشکده مهندسی مکانیک، دانشگاه تربیت مدرس

2 عضو هیات علمی / دانشکده مهندسی مکانیک، دانشگاه تربیت مدرس

چکیده

با توجه به اینکه سرعت جریان هوا در محفظه احتراق موتورهای اسکرمجت‌ مافوق‌صوت است، لذا زمان کافی برای آمیختگی مناسب سوخت و هوا در این سرعت‌های بالا وجود ندارد، و بررسی فرآیند آمیختگی سوخت و هوا در این شرایط یکی از موضوعات مهم در طراحی موتورهای اسکرمجت است. یکی از روش‌های پر کاربرد پاشش سوخت در جریان‌های مافوق صوت محفظه‌های احتراق موتورهای اسکرمجت، روش پاشش متقاطع سوخت در جریان عبوری مافوق صوت است. از آنجاییکه در اینگونه جریان‌ها، سرعت هوای عبوری بسیار زیاد است، دستیابی به آمیختگی مناسب جهت احتراق از مسائل چالش بر انگیز می باشد. در کار حاضر با استفاده از حل معادلات سه-بعدی ناویر-استوکس رینولدز-متوسط به همراه مدل آشفتگی k-ω sst و معادله حالت گاز ایده آل، حوزه جریان پاشش متقاطع در جریان عبوری مافوق صوت به صورت عددی شبیه‌سازی شده است و تأثیر قطر پاشش بر ویژگی‌های آمیختگی از قبیل عمق نفوذ سوخت، راندمان آمیختگی، نسبت مساحت آمیختگی مؤثر و تلفات فشار سکون بررسی شده است. سپس نتایج شبیه‌سازی‌های جریان واکنش‌پذیر نیز ارائه شده است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Investigation of the effect of injection diameter on the characteristics of the flowfield of transverse injection into supersonic air crossflow

نویسندگان [English]

  • Mostafa Zahedzadeh 1
  • Fathollah Ommi 2
1 Tarbiat Modares University
2 Professor, Mechanical Engineering Department, Tarbiat Modares University
چکیده [English]

Due to the fact that the velocity of air flow in the combustion chamber of scramjets is supersonic, so there is not enough time for proper mixing of fuel and air at these high speeds, and studying the process of mixing of fuel and air in this situation is one of the important issues for scramjet engine design. One of the most widely used methods of fuel injection in supersonic flows of scramjet engine combustion chambers is the method of transverse injection into supersonic air crossflow. Since the velocity of the passing air is very high in such streams, it is challenging to achieve a suitable mixture for combustion. In the present work, by solving the three-dimensional Reynolds-Averaged-Navier-Stokes equations with the k-ω sst turbulence model and the ideal gas state equation, the transverse injection domain in the supersonic flow is numerically simulated and the effect of injection diameter is investigated based on the mixing properties such as fuel penetration depth, mixing efficiency, effective mixing area ratio and stagnation pressure losses. After that, results of reactive flow are presented.

کلیدواژه‌ها [English]

  • Transverse injection
  • Supersonic flow
  • Mixing efficiency
  • Injection diameter

مراجع

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