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بررسی تأثیر مشخصه‌های هندسی بر جریان داخل کانال در شرایط جریان مافوق‌صوت غیرواکنشی با حضور حفره | ||
| نشریه مهندسی مکانیک امیرکبیر | ||
| مقاله 6، دوره 53، شماره 11، بهمن 1400، صفحه 5409-5428 اصل مقاله (1.67 M) | ||
| نوع مقاله: مقاله پژوهشی | ||
| شناسه دیجیتال (DOI): 10.22060/mej.2021.19574.7062 | ||
| نویسندگان | ||
| وحیده دشتی رحمت آبادی1؛ محسن آقا سید میرزا بزرگ2؛ سعید خردمند* 3 | ||
| 1دانشجوی دکترا- دانشگاه مالک اشتر | ||
| 2عضو هیئت علمی دانشگاه مالک اشتر، دانشیار | ||
| 3دانشگاه صنعتی مالک اشتر*مکانیک | ||
| چکیده | ||
| در کار حاضر، به بررسی جریان داخل یک کانال دارای حفره به عنوان محفظه احتراق یک موتور اسکرمجت پرداخته شده است. تحلیل‌های انجام شده در این تحقیق در خصوص تأثیر مشخصه‌های هندسی وابسته به حفره نظیر L/D (طول به عمق حفره)، H/D ( ارتفاع کانال به عمق حفره) و عددهای ماخ متفاوت در محدوده مافوق‌صوت بر روی کیفیت جریان داخل کانال محفظه احتراق است. در جریان غیرواکنشی مورد بررسی در این مقاله، مشخصه گردش به عنوان مشخصه وابسته به اختلاط تحلیل شده است. در تحلیل عددی، از معادلات دو بعدی ناویر استوکس به منظور حل جریان پایا و روش چگالی مبنا استفاده شده و مدل اغتشاشی مورد استفاده، روش k-ɛ استاندارد بوده است. به منظور شبیه سازی عددی از نرم افزار انسیس فلوئنت نسخه 18/2 استفاده شده است. نتایج به دست آمده نشان می‌دهد که با افزایش نسبت L/D، افزایش عدد ماخ و وجود زاویه در دیواره عقبی حفره، میزان گردش در لایه‌مرزی و در نتیجه اختلاط افزایش می‌یابد. هندسه‌های دارای H/D بزرگ‌تر، عملکرد بهتری را نسبت به سایر هندسه‌های مورد بررسی در مورد میزان تولید گردش و کاهش افت فشار کل از خود نشان دادند. همچنین با وجود اینکه نسبت H/D برابر با 1، گردش بیشتری نسبت به حالات دیگر دارد اما به دلیل بقای شوک مایل در برخی شرایط و ایجاد افت فشار کل قابل توجه، استفاده از آن در همه ماخ‌های مافوق‌صوت مطمئن نخواهد بود. | ||
| کلیدواژه‌ها | ||
| جریان مافوق‌صوت؛ حفره؛ غیر واکنشی؛ زاویه دیواره عقبی حفره؛ نسبت H/D و L/D | ||
| عنوان مقاله [English] | ||
| Investigation of Geometric Characteristics on the Non-Reaction Supersonic Flow inside the Channel with the Presence of Cavities | ||
| نویسندگان [English] | ||
| Vahideh Dashti Rahmat Abadi1؛ Mohsen A.S. Mirzabozorg2؛ Saeed Kheradmand3 | ||
| 1PHD Student, Malek Ashtar Uni. | ||
| 2Aerospace Department, Associated Professor | ||
| 3Mech. Dept., MUT, Iran | ||
| چکیده [English] | ||
| In the present work, the flow inside a channel with a cavity is investigated as a Scramjet combustion chamber. For this aim, the parameters such as L/D (cavity length to cavity depth), H/D (channel height to cavity depth), and varied Mach numbers are studied in the supersonic flow to investigate the effect of geometric parameters on channel flow in non- reacting conditions. In this work, vorticity is used as a mixing parameter. Two-dimensional Navier-Stokes equations are used to solve the steady-state flow. The density based method and standard k-ε Model are employed for numerical simulation. The results show that vorticity of boundary layer and thus mixing in flow is increased with growing of L/D, Mach number and having sweep angle for the cavity. Geometries with larger H/D performed better than other geometries in terms of generating vorticity and reducing Total pressure loss. Although the H/D = 1 ratio has a higher recirculation than others, it will not be reliable for all supersonic flow because of its considerable total pressure loss and the survival of the oblique shock in some conditions. | ||
| کلیدواژه‌ها [English] | ||
| Supersonic flow, Cavity, Non- reaction, Aft angle of cavity, L/D and H/D ratio | ||
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| مراجع | ||
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