کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
7153855 | 1462492 | 2017 | 8 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
Unsteady supercritical/critical dual flowpath inlet flow and its control methods
ترجمه فارسی عنوان
جریان ورودی جریان دوگانه فوق بحرانی / بحرانی دو طرفه و روش کنترل آن
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کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه
سایر رشته های مهندسی
مهندسی هوافضا
چکیده انگلیسی
The characteristics of unsteady flow in a dual-flowpath inlet, which was designed for a Turbine Based Combined Cycle (TBCC) propulsion system, and the control methods of unsteady flow were investigated experimentally and numerically. It was characterized by large-amplitude pressure oscillations and traveling shock waves. As the inlet operated in supercritical condition, namely the terminal shock located in the throat, the shock oscillated, and the period of oscillation was about 50â¯ms, while the amplitude was 6â¯mm. The shock oscillation was caused by separation in the diffuser. This shock oscillation can be controlled by extending the length of diffuser which reduces pressure gradient along the flowpath. As the inlet operated in critical condition, namely the terminal shock located at the shoulder of the third compression ramp, the shock oscillated, and the period of oscillation was about 7.5â¯ms, while the amplitude was 12â¯mm. At this condition, the shock oscillation was caused by an incompatible backpressure in the bleed region. It can be controlled by increasing the backpressure of the bleed region.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Chinese Journal of Aeronautics - Volume 30, Issue 6, December 2017, Pages 1877-1884
Journal: Chinese Journal of Aeronautics - Volume 30, Issue 6, December 2017, Pages 1877-1884
نویسندگان
Jun LIU, Huacheng YUAN, Yunfei WANG, Ning GE,