تأثیر شیارهای محیطی بر عملکرد یک کمپرسور گذرصوتی

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشگاه امیرکبیر

2 انستیتوی مکانیک و دینامیک سیالات، دانشگاه فرایبرگ، فرایبرگ، آلمان

3 دانشکده هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران

چکیده

در این مقاله به مطالعه عددی اصلاح پوسته با کمک شیارهای محیطی در یک فن گذرصوتی پرداخته شده‌است. چهار شیار محیطی در بالای یک پره ناسا 67قرار داده‌شده و شبیه‌سازی‌های گذرا از نقطه خفگی تا نزدیکی واماندگی صورت گرفته‌است. نتایج نشان می‌دهد شیارهای محیطی باعث کاهش زاویه برخورد در لبه حمله پره می‌شوند. همچنین، شوک و جریان نشتی نوک پره به پایین دست جریان رانده می‌شوند. شیارها از یک طرف باعث افزایش مومنتوم در جهت جریان می‌شوند (جریان از پایین دست شیارها وارد و از بالادست آنها خارج و به جریان اصلی تزریق می‌شود) و از طرف دیگر باعث ایجاد یک مسیر جریان بین سطوح فشاری و مکشی در نوک پره (و در نتیجه کاهش اختلاف فشار این سطوح) می‌شوند. در پژوهش حاضر مشاهده شد که در نزدیکی نقطه واماندگی، میدان جریان در شیارها بسیار ناپایا است. نتایج نشان داد که بیشترین رفتار ناپایا در اولین شیار است که تغییرات زمانی دبی جرمی عبوری از این شیار در حدود 30 درصد میانگین زمانی دبی جرمی آن است. لذا برای شبیه‌سازی اصلاح پوسته کمپرسور به کمک شیارهای محیطی باید از حل ناپایا استفاده کرد و حل دائمی کافی نیست.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Circumferential Casing Treatment in a Transonic Fan

نویسندگان [English]

  • Hosein Khaleghi 1
  • Martin Heinrich 2
  • Mohammad Javad Shahriyari 3
1 Department of Aerospace Engineering, Amirkabir University of Technology, Tehran
2 Institute of Mechanics and Fluid Dynamics, Technische Universität Bergakademie Freiberg, 09599 Freiberg, Germany
3 Department of Aerospace Engineering, Amirkabir University of Technology, Tehran 15875-4413, Iran
چکیده [English]

This paper reports on a numerical simulation of circumferential groove casing treatment in a high-speed axial fan. Four circumferential grooves of the same geometry are located over the tip of a NASA Rotor-67 and unsteady calculations are performed from choke to near-stall. Results show that circumferential grooves reduce the incidence angle near the pressure surface at the blade leading-edge. Furthermore, the passage shock and the leakage flow are pushed rearward in the passage. It is found that circumferential grooves increase the momentum in the streamwise direction (fluid is absorbed by the grooves from their downstream part and is injected from their upstream section). The grooves also provide a flow path between the suction and pressure surface, leading to a reduction in the pressure difference between them. At the near-stall point the flow field near the grooves was found to be highly unsteady. Maximum unsteadiness was observed in the first upstream groove: the circulated mass flow rate changed as high as roughly 30 percent of its time-averaged value. As a result, in order to simulate circumferential groove casing treatment in compressors, unsteady computations are required.

کلیدواژه‌ها [English]

  • Circumferential groove
  • Range Extension
  • Casing Treatment
  • Transonic Compressor
  • NASA Rotor-67
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