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مطالعه عددی اثرات فاصله نوک پره بر عملکرد یک کمپرسور محوری چند مرحلهای گذرصوتی | ||
| نشریه مهندسی مکانیک امیرکبیر | ||
| دوره 57، شماره 2، 1404، صفحه 187-214 اصل مقاله (3.15 M) | ||
| نوع مقاله: مقاله پژوهشی | ||
| شناسه دیجیتال (DOI): 10.22060/mej.2025.23795.7821 | ||
| نویسندگان | ||
| علی حسن زاده بافقی؛ محمد جواد شهریاری؛ حسین خالقی* | ||
| دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران | ||
| چکیده | ||
| کمپرسورها که به منظور افزایش فشار گاز مورد استفاده قرار میگیرند در صنعت از اهمیت فراوانی برخوردار بوده و ممکن است به عنوان بخشی از یک ماشین بزرگتر مانند توربین گاز و یا به عنوان یک ماشین مجزا در واحدهای فرآیندی مورد استفاده قرار گیرند. با توجه به کاربرد فراوان کمپرسورها، بهبود عملکرد و افزایش بازه عملکردی آنها اهمیت فراوانی دارد و مطالعات زیادی در این زمینه و عوامل موثر بر آن انجام شده است. در این مطالعه، اثر فاصله نوک پره از پوسته بر عملکرد یک کمپرسور چند طبقه گذرصوتی با استفاده از شبیهسازی عددی مورد بررسی قرار گرفته است. ابتدا یک کمپرسور مبنای ناسا با دادههای موجود شبیهسازی و صحتسنجی شد. همچنین یک بررسی و صحتسنجی از طریق شبیهسازی تک طبقه هر یک از طبقات کمپرسور و مقایسه آن با نتایج شبیهسازی چند طبقه انجام شده است. سپس تأثیر افزایش لقی روتورها به 1/5 و 2 برابر حالت مبنا، در سه حالت مختلف (افزایش لقی در همه روتورها، تنها روتور اول یا تنها روتور دوم) بررسی گردیده است. نتایج نشاندهنده آن است که از بین این دو روتور، روتور با لقی بیشتر همان روتور عامل ناپایداری است و همچنین بازه عملکردی کمپرسور در مقایسه با شرایطی که لقی همه روتورها به یک اندازه افزایش یابد تقریبا مشابه است. | ||
| کلیدواژهها | ||
| کمپرسور چند طبقه؛ گذرصوتی؛ شبیهسازی عددی؛ لقی؛ ناپایداری؛ بازه عملکردی | ||
| عنوان مقاله [English] | ||
| A Numerical Study of the Effects of Blade Tip Clearance on the Performance of a Multi-Stage Transonic Axial Compressor | ||
| نویسندگان [English] | ||
| Ali Hassanzadeh Bafghi؛ Mohammad Javad Shahriyari؛ Hosein Khaleghi | ||
| Department of Aerospace Engineering, Amirkabir University of Technology, Tehran 15875-4413, Iran | ||
| چکیده [English] | ||
| Compressors are integral components in various industrial systems, ranging from standalone units in process plants to essential parts of gas turbines. Given the widespread application of compressors, improving their performance and expanding their operating range are of great importance, leading to extensive studies on this subject and the factors affecting it. In this study, the effect of blade tip clearance on the performance of a transonic multistage compressor was investigated using numerical simulation. First, a baseline NASA compressor was simulated and validated using available data. Additionally, a single-stage simulation of each compressor stage was conducted and validated by comparison with the multi-stage simulation results. Subsequently, the impact of increasing rotor clearances to 1.5 and 2 times the baseline level was examined in three different scenarios: increasing clearance for all rotors, only the first rotor, or only the second rotor. The results indicate that among these two rotors, the one with the larger clearance is the primary source of instability. Furthermore, the operating range of the compressor remains almost unchanged compared to the scenario where the clearance of all rotors is increased uniformly. | ||
| کلیدواژهها [English] | ||
| Multistage Compressor, Transonic, Numerical Simulation, Clearance, Instability, Operating Range | ||
| مراجع | ||
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