| 进气道动态畸变被动控制技术的初步研究 |
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| 引用本文： | 黄熙君,彭旭.进气道动态畸变被动控制技术的初步研究[J].推进技术,1991,12(6):10-16. |
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| 作者姓名： | 黄熙君 彭旭 |
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| 作者单位： | 北京航空航天大学
(黄熙君)，北京航空航天大学(彭旭) |
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| 摘 要： | 对S型进气道扩压器在临界及超临界工况下的流动特性进行了研究,通过研究了解超临界工况下动态畸变的形成和变化特征.国内外的研究均表明:进气道内激波与附面层的相互干扰是引起动态畸变的主要原因之上,因而本文中采用壁面处理被动控制技术进行激波与附面层干扰的控制,用以抑制动态畸变.研究结果表明:在较大的超临界工况下,该控制技术可明显地抑制激波的失稳和振荡,从而使动态畸变的气流脉动峰值下降约60%.
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| 关 键 词： | 进气道 流场畸变 控制 扩压器 航空发动机 |
PRELIMINARY INVESTIGATION OF INLET DYNAMIC DISTORTION AND IT'S PASSIVE CONTROL |
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| Huang Xijin and Peng Xu.PRELIMINARY INVESTIGATION OF INLET DYNAMIC DISTORTION AND IT''''S PASSIVE CONTROL[J].Journal of Propulsion Technology,1991,12(6):10-16. |
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| Authors: | Huang Xijin and Peng Xu |
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| Institution: | Beijing University of Aeronautics and Astronautics |
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| Abstract: | In this paper,the inlet diffuser flow under critical and supercritical operation condition was studied. From the investigation of supercritical operation condition the formation and charactiristic of dynamic distortion have been understanded. The dynamic distortion of inlet diffuser mainly is caused by interaction of shock wave with boundary layer.A passive control method was used to reduce the interaction of shock wave with boundary layer. The results of experiments show that under very supercritical operation condition the passive control method obviously reduces the unsteadyness and oscillation of terminal shock wave in diffuser, and the peak value of pressure fluctuation decreases by about 60%. |
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| Keywords: | Inlet Flow distortion Control |
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