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Active noise control of supersonic impinging jet using pulsed microjets

机译:利用脉冲微喷射控制超音速撞击射流的主动噪声

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摘要

This thesis concerns an active noise control of supersonic impinging jet flow using unsteady microjet injection. Supersonic impinging jet involves several problems such as lift loss, ground erosion, significant noise pollution, and sonic fatigue, all of which are dominated by impinging tones mainly caused by well-known phenomenon, the feed back loop. The main goal of this study is to achieve uniform and consistent noise reduction in the entire range of jet operating condition, by means of intercepting this feed back loop. Experimental investigations on ideally expanded Mach number 1.5, supersonic impinging jet flow were carried out at the scaled supersonic experimental facility. The actuator used for active control is composed of pulsed microjets, utilizing a fraction of mass flow rate needed with steady microjets. Two means of producing pulsed microjet were introduced; one with a rotating cap, pulsing at 16 - 100Hz, and the other developed based on the principle of Hartmann tube, pulsing at 4.4 - 6.1kHz, referred to as high frequency actuator. Control parameters related to pulsed microjet injection with rotating cap were varied to evaluate their effects on suppression of impinging tones, whereas the effect of high frequency actuator is shown only as an initial step and needs further investigation in the future. For pulsed microjet with rotating cap, mass flow rate, directly proportional to the supply pressure of microjet, is found to be the most important parameter amongst all and saturated supply pressures for steady and pulsed microjet are demonstrated. It is demonstrated that pulsed microjet gives more noise reduction than steady microjet with the same mass flow rate, at certain range of supply pressure, and also that pulsed microjet could be as effective on suppression of impinging tones as steady microjet with less mass flow rate. In addition, the effect of pulsed microjet on hot temperature impinging jet was examined since the jet is much hotter than ambient air in reality. The concept of extremum control strategy is introduced to more efficiently find an optimal pulsing condition for uniform and consistent noise reduction.
机译:本文涉及使用不稳定的微射流注入对超声速冲击射流的主动噪声控制。超音速撞击射流涉及多个问题,例如升力损失,地面侵蚀,严重的噪音污染和声音疲劳,所有这些问题主要是由众所周知的现象(即反馈回路)引起的撞击声引起的。这项研究的主要目标是通过拦截此反馈回路,在整个喷气机运行状况范围内实现一致且一致的降噪。在规模超音速实验设备上进行了理想扩展的1.5马赫数,超音速撞击射流的实验研究。用于主动控制的执行器由脉冲式微喷射器组成,利用稳定的微喷射器所需的一部分质量流量。介绍了两种产生脉冲微喷的方法:一种是带旋转帽的,脉冲频率为16-100Hz,另一种是根据Hartmann管原理开发的,脉冲为4.4-6.1kHz,被称为高频执行器。改变了与带有旋转帽的脉冲微喷射注入相关的控制参数,以评估其对撞击音抑制的影响,而高频执行器的作用仅作为初始步骤显示,将来需要进一步研究。对于具有旋转盖的脉冲微喷射器,发现质量流量与微喷射器的供气压力成正比,是其中最重要的参数,并证明了稳定和脉冲式微喷射器的饱和供气压力。结果表明,在一定的供应压力范围内,脉冲微喷比相同质量流量的稳定微喷具有更大的降噪效果,而且脉冲微喷在抑制撞击声方面与质量流量较小的稳定微喷一样有效。另外,检查了脉冲微射流对撞击高温的射流的影响,因为实际上该射流比环境空气要热得多。引入极值控制策略的概念是为了更有效地找到最佳脉冲条件,以实现均匀一致的降噪。

著录项

  • 作者

    Hong Seung Hyuck;

  • 作者单位
  • 年度 2009
  • 总页数
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类

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