超声速民机发动机短舱布局对声爆的影响  

Effect of engine nacelle layout on sonic boom of supersonic transport

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作  者:肖天航[1] 徐雅楠 朱震浩 邓双厚[1] XIAO Tianhang;XU Yanan;ZHU Zhenhao;DENG Shuanghou(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区:[1]南京航空航天大学航空学院,南京210016

出  处:《北京航空航天大学学报》2023年第9期2267-2278,共12页Journal of Beijing University of Aeronautics and Astronautics

基  金:航天进入减速与着陆技术实验室开放基金(EDL19092111);国家自然科学基金(11672133);陕西省自然科学基础研究计划(2021JQ-078)。

摘  要:超声速民机较高的飞行速度导致发动机短舱与机翼机身存在强烈的气动干扰,且高速喷流会改变主流的激波系结构,进而影响声爆强度。以超声速民机为研究对象,对不同短舱布局开展数值模拟研究,揭示发动机短舱位置、数量对近场过压信号特性的影响规律。数值模拟运用有限体积法在直角网格上求解流体控制方程进行,通过伴随自适应网格加密生成高分辨率网格以精确捕捉近场过压信号。结果表明:发动机进气道唇口激波、尾喷口后缘激波及尾喷流与机体机翼引起的激波系存在强烈的相互干扰,一定程度上增加了近场过压幅值,从而增强了声爆强度。短舱沿弦向前移及置于机翼上方可以有效降低声爆强度,沿展向外移通过抑制尾部各激波的合并也可有效降低声爆强度;在相同总推力前提下,相比三发构型,双发构型能有效降低后体激波强度,但较大尺寸的短舱引起较强的进气道唇口激波。综合考虑喷流噪声和气动阻力因素,翼下双发布局对于新一代超声速民机并非最佳选项。The strong aerodynamic interaction between the nacelles and the wing-body at supersonic speed,and the effect of the exhaust plume on the mainstream shock wave structure could have a great influence on the sonic boom loudness.This paper carries out a numerical investigation on the effect of nacelle layout on thesonic boom for a supersonic transport configuration where the supersonic flows and near field pressure signatures are computed by using a finite volume solver and an adjoint-based Cartesian adaptive mesh refinement method.Various relative positions of nacelles with respect to the wing andthe different number of nacelles are considered.Results indicate that the shock and expansion waves caused by the wing-body combination are significantly interfered with by the lip shock at the inlet,the nozzle trailing edge shock,and the expansion and aft shock of the nozzle plume.This increases the amplitude of the pressure signatures and subsequently increases the sonic boom loudness.Compared with the baseline,the ground loudness can be effectively suppressed by moving the nacelles forward along the chord,outward along the span-wise,and mounting above the wing.Under the same overall force and with the same number of engines and nacelles,the configuration with twin nacelles can reduce the aft shock,but the larger nacelle results in a stronger lip shock at the intake,increasing the loudness of the sonic boom.Thus,considering the engine noise and aerodynamic drag,it is not recommended to deploy twin nacelles for next-generation supersonic transport.

关 键 词:超声速民机 短舱布局 声爆 网格自适应 笛卡儿网格 

分 类 号:V221.3[航空宇航科学与技术—飞行器设计] TB553[理学—物理]

 

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