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An experimental investigation of supersonic rectangular over-expanded nozzle of single and two-phase flows.

机译:单相和两相流超声速矩形过膨胀喷嘴的实验研究。

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This dissertation presents the results of an experimental investigation of the supersonic rectangular over-expanded flow of single and two-phase flows. Recent interest in rectangular supersonic jets is motivated by the need to reduce plume length and acoustically excited structural loads in the exhaust system of high performance aircrafts. Semi-periodic shock structures form in the jet plumes of these vehicles during low speed flight at off design conditions. These shock cells affect the jet velocity and temperature decay as well as the jet spread rate and its acoustic field. The flow regimes and shock structure in the plume was characterized for jets in quiescent atmosphere at overexpanded conditions. Instantaneous and phase average schlieren/shadowgraph images of the internal flow and the jets are presented to show the over-expanded shock structure and jet spread rate at different nozzle pressure ratios ranged from 1.6 to 9.5.; A high-pressure particle feeders have been constructed to steady feed the dispersed large particles and the seeding particle for LDA measurements at different particle loading rates. Schlieren pictures of the jets are presented to show the shock structure and jet spread rate. LDV measurements are presented for the jet flow field and the centerline velocity decay. The results indicate that the rectangular supersonic jet spread rate is greater along the minor axis and increases with the nozzle pressure ratio. The individual shock cell length, as well as the total number of shock cells within the jet plume were found to increase with nozzle pressure ratio. In two-phase rectangular jets of gas and dispersed solid particles the shock strength was found to attenuate with increased particle loading. The design, construction and initial shakedown of the facility has been accomplished. The effort required to reach this stage has been greater than initially expected. Further more detailed data acquisitions and measurements will be accomplished in future studies.
机译:本文提出了单相和两相流超声速矩形超扩流实验研究的结果。对矩形超音速喷气机的最新兴趣是由于需要减少高性能飞机的排气系统中的羽状长度和声激发结构载荷。在非设计条件下的低速飞行过程中,这些车辆的喷射羽流中会形成半周期的冲击结构。这些冲击单元会影响射流速度和温度衰减以及射流扩散速率及其声场。羽流中的流态和冲击结构是针对静态条件下过膨胀条件下的射流的特征。瞬时和相位平均内部流和射流的影线/阴影图图像显示了在1.6至9.5范围内的不同喷嘴压力比下,过度膨胀的冲击结构和射流散布速率。已经构造了高压颗粒进料器,以稳定地进料分散的大颗粒和播种颗粒,以便在不同的颗粒加载速率下进行LDA测量。射流的Schlieren图片显示了冲击结构和射流扩散速率。提出了针对射流流场和中心线速度衰减的LDV测量。结果表明,矩形超音速射流扩展率沿短轴方向更大,并随喷嘴压力比的增加而增大。发现单个冲击池的长度以及射流羽流中冲击池的总数随喷嘴压力比的增加而增加。在气体和分散的固体颗粒的两相矩形射流中,发现冲击强度随着颗粒负载的增加而减弱。该设施的设计,建造和初始安装已完成。达到此阶段所需的努力比最初预期的要大。更多详细的数据采集和测量将在以后的研究中完成。

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