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亚音速喷流出口扰动对湍流与声场模拟的影响 被引量:3
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作者 许聪 刘琪麟 赖焕新 《华东理工大学学报(自然科学版)》 CAS CSCD 北大核心 2021年第4期510-518,共9页
采用大涡模拟方法计算出口马赫数Ma=0.75、雷诺数Re D=8.7×105的圆口喷射流动,研究了改进的来流多模态线性不稳定扰动和涡环扰动对促成转捩、湍流特性以及远声场结果的影响。研究结果表明,与来流无扰动的情况相比,两种扰动方式均... 采用大涡模拟方法计算出口马赫数Ma=0.75、雷诺数Re D=8.7×105的圆口喷射流动,研究了改进的来流多模态线性不稳定扰动和涡环扰动对促成转捩、湍流特性以及远声场结果的影响。研究结果表明,与来流无扰动的情况相比,两种扰动方式均有利于破坏喷口环状涡的周向稳定性,从而加速剪切层转捩,逼近实际喷口的湍流状态;且多模态线性不稳定扰动工况的喷口速度脉动水平高于涡环扰动下的喷流,能更早地触发转捩。从远声场的结果来看,两种扰动方法有效地减少了计算模型中因转捩和涡配对而导致的低频噪声误差,从而吻合实验数据。 展开更多
关键词 扰动影响 亚音速喷流 大涡模拟 剪切层转捩 涡配对
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使用喷管内壁盲孔控制亚音速喷流噪声 被引量:2
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作者 施智晓 赖焕新 《华东理工大学学报(自然科学版)》 CAS CSCD 北大核心 2018年第5期775-782,共8页
研究了亚音速喷流的流动特性及外声场特性。针对亚音速喷流的噪声传播及分布特性,设计了多种内壁盲孔延伸构件,试图通过产生喷流出口处流动的不均匀性进而影响喷流噪声。通过试验测试,得到了不同孔径D、孔深H的盲孔延伸构件对马赫数(Ma)... 研究了亚音速喷流的流动特性及外声场特性。针对亚音速喷流的噪声传播及分布特性,设计了多种内壁盲孔延伸构件,试图通过产生喷流出口处流动的不均匀性进而影响喷流噪声。通过试验测试,得到了不同孔径D、孔深H的盲孔延伸构件对马赫数(Ma)为0.6的亚音速喷流远近声场的影响。结果表明,相同开孔分布情况下,孔径的增大对外声场的影响效果更为显著,而孔深的变化则对噪声频谱产生两种不同的影响效果。本文的测量结果为进一步分析多孔结构件降噪效果提供了基础,并为改变不同频段噪声的相关应用提供了参考。 展开更多
关键词 亚音速喷流 噪声 声场测试 盲孔 噪声频谱
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多孔空腔结构对亚音速喷流噪声影响的研究 被引量:2
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作者 施智晓 许聪 赖焕新 《工程热物理学报》 EI CAS CSCD 北大核心 2019年第3期559-564,共6页
本文实验研究亚音速圆口喷流噪声的一种被动控制方法。将喷管内壁改造成多孔板与后方容腔组合的结构,研究这种被动措施对声源流场与辐射声场的影响。设计制作了多种"多孔内壁+空腔的组合延伸构件,与不包括这种多孔处理的基础喷管... 本文实验研究亚音速圆口喷流噪声的一种被动控制方法。将喷管内壁改造成多孔板与后方容腔组合的结构,研究这种被动措施对声源流场与辐射声场的影响。设计制作了多种"多孔内壁+空腔的组合延伸构件,与不包括这种多孔处理的基础喷管相比较,在喷流出口马赫数同为Ma=0.5的情况下,分析了这些"多孔内壁+空腔"延伸构件的孔径D、孔深H以及空腔厚度T对喷流远声场的影响与变化趋势,为采用这种方法控制喷流噪声的实际应用提供了初步的依据。 展开更多
关键词 亚音速喷流 壁面多孔化 气动噪声 噪声控制
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喷流噪声控制实验研究 被引量:1
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作者 郑克扬 桂辛民 《燃气涡轮试验与研究》 1991年第1期21-28,共8页
本文着重研究喷流噪声形成机理及工程计算方法。通过细致实验,研究了声动率与喷流速度的关系,验证和完善了Lighthill和Lilley等经验式。同时对喷流噪声指向性,谱特性进行了分析。最后对喷流噪声引射式消声器进行了较为深入的研究。
关键词 亚音速喷流 气动噪声 引射式消声器 声功率 速度 指向性 谱特性 抑制 理论
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On the Existence and Stability of a Global Subsonic Flow in a 3D Infinitely Long Cylindrical Nozzle 被引量:1
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作者 Gang XU Huicheng YIN 《Chinese Annals of Mathematics,Series B》 SCIE CSCD 2010年第2期163-190,共28页
This paper is concerned with the problem on the global existence and stability of a subsonic flow in an infinitely long cylindrical nozzle for the 3D steady potential flow equation. Such a problem was indicated by Cou... This paper is concerned with the problem on the global existence and stability of a subsonic flow in an infinitely long cylindrical nozzle for the 3D steady potential flow equation. Such a problem was indicated by Courant-Friedrichs in [8, p. 377]: A flow through a duct should be considered as a cal symmetry and should be determined steady, isentropic, irrotational flow with cylindriby solving the 3D potential flow equations with appropriate boundary conditions. By introducing some suitably weighted HSlder spaces and establishing a priori estimates, the authors prove the global existence and stability of a subsonic potential flow in a 3D nozzle when the state of subsonic flow at negative infinity is given. 展开更多
关键词 Subsonic flow Potential flow equation Bessel function Weighted HSlder space Global existence
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Effects of Nozzle-Strut Integrated Design Concepton on the Subsonic Turbine Stage Flowfield 被引量:3
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作者 LIU Jun DU Qiang +2 位作者 LIU Guang WANG Pei ZHU Junqiang 《Journal of Thermal Science》 SCIE EI CAS CSCD 2014年第5期494-504,共11页
In order to shorten aero-engine axial length,substituting the traditional long chord thick strut design accompanied with the traditional low pressure(LP) stage nozzle,LP turbine is integrated with intermediate turbine... In order to shorten aero-engine axial length,substituting the traditional long chord thick strut design accompanied with the traditional low pressure(LP) stage nozzle,LP turbine is integrated with intermediate turbine duct(ITD).In the current paper,five vanes of the first stage LP turbine nozzle is replaced with loaded struts for supporting the engine shaft,and providing oil pipes circumferentially which fulfilled the areo-engine structure requirement.However,their bulky geometric size represents a more effective obstacle to flow from high pressure(HP) turbine rotor.These five struts give obvious influence for not only the LP turbine nozzle but also the flowfield within the ITD,and hence cause higher loss.Numerical investigation has been undertaken to observe the influence of the Nozzle-Strut integrated design concept on the flowfield within the ITD and the nearby nozzle blades.According to the computational results,three main conclusions are finally obtained.Firstly,a noticeable low speed area is formed near the strut's leading edge,which is no doubt caused by the potential flow effects.Secondly,more severe radial migration of boundary layer flow adjacent to the strut's pressure side have been found near the nozzle's trailing edge.Such boundary layer migration is obvious,especially close to the shroud domain.Meanwhile,radial pressure gradient aggravates this phenomenon.Thirdly,velocity distribution along the strut's pressure side on nozzle's suction surface differs,which means loading variation of the nozzle.And it will no doubt cause nonuniform flowfield faced by the downstream rotor blade. 展开更多
关键词 Intermediate Turbine Duct Integrated Design Concept Flowfield Analysis Total Pressure Loss Analysis
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