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Analysis of liner performance using the NASA Langley Research Center Curved Duct Test Rig

机译：使用NASA兰利研究中心弯曲风管试验台进行衬管性能分析

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The NASA Langley Research Center Curved Duct Test Rig (CDTR) is designed to test aircraft engine nacelle liner samples in an environment approximating that of the engine on a scale that approaches the full scale dimensions of the aft bypass duct. The modal content of the sound in the duct can be determined and the modal content of the sound incident on the liner test section can be controlled. The effect allow speed, up to Mach 0.5 in the test section, can be investigated. The results reported in this paper come from a study to evaluate the effect of duct configuration on the acoustic performance of single degree of freedom (SDOF) perforate-over-honeycomb liners. Variations of duct configuration include: asymmetric (liner on one side and hard wall opposite) and symmetric (liner on both sides) wall treatment; inlet and exhaust orientation, in which the sound propagates either against or with the flow; and straight and curved (outlet is offset from the inlet by one duct width) flow path. The effect that duct configuration has on the overall acoustic performance is quantified. The redistribution of incident mode content is shown, in particular the mode scatter effect that liner symmetry has on symmetric and asymmetric incident mode shapes. The Curved Duct Test Rig is shown to be a valuable tool for the evaluation of acoustic liner concepts. (C) 2015 Elsevier Ltd. All rights reserved.
机译：NASA兰利研究中心弯曲风管试验台（CDTR）旨在在接近后方旁通管满刻度尺寸的规模下，在接近发动机的环境中测试飞机发动机机舱衬里样品。可以确定管道中声音的模态含量，并且可以控制入射到衬管测试段上的声音的模态含量。可以研究在测试部分中允许速度达到0.5马赫的效果。本文报道的结果来自一项研究，以评估导管结构对单自由度（SDOF）多孔蜂巢式衬管的声学性能的影响。管道配置的变化包括：不对称（一侧为内衬，而硬壁相对）和对称（两侧为内衬）壁处理；进气和排气方向，声音在气流中传播或逆着气流传播；直线和弯曲（出口从入口偏移一个导管宽度）的流动路径。量化了导管结构对整体声学性能的影响。显示了入射模态内容的重新分布，尤其是线性对称对对称和非对称入射模态形状的模式散射效应。曲线风管试验台被证明是评估声学衬管概念的有价值的工具。 （C）2015 Elsevier Ltd.保留所有权利。

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