射流气动声场宏观与微观方法的研究及其应用
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摘要
射流气动噪声问题引起了越来越多的关注，本文从宏观与微观角度出发，分别用FEM、FVM、LBM、MDM和谐振子方法等研究射流气动声场问题，并作了某些研究探索。
对于贯流风机非轴对称射流组成的受限空间旋转射流气动声场，本文用宏观传统的气动声学计算方法，研究了它的旋转射流特性及其房间流场的气流组织，数值分析和实验测量了因流动致声的有关对应监测特征点的静压频谱及功率谱密度分布。
对于轴对称管道旋转射流流动，采用定常—非定常—LES的大涡模拟方案，研究了旋转射流特性、压力频谱与声压及其声传播问题。动叶的卡门涡和叶顶泄漏涡，以及叶片前缘产生的近壁叶道涡是动叶组特色涡。涡声的源头位于前缘和尾缘。流场外侧的湍流粘性和有效粘性均大于中部，加剧了声音耗散，声压的幅射重点指向轴线四周。
对于轴对称圆射流运动，本文用有限元方法构造了三维圆喷嘴模型。在射流出口设置空气的阻抗边界条件，用Skyline求解方法，对三种高雷诺数流动和两种低雷诺数流动进行数值分析，用以描述流场对应的声模态和对应频域的声场信息。圆射流的声压是以声阻抗率为特性的传播，呈现测量的退相干性。射流的声模态与管嘴的结构模态在大雷诺数下的高频率段重叠交叉，耦合作用不明显。大雷诺数下的声压指向性呈弱的非轴对称结构，而小雷诺数高马赫数的声压指向在近场是球形的。在高频部分的下游传递出锥状逆波，破坏了轴线两侧的波阵面，尤其是在上游轴线周侧。
本文用介观方法对射流气动声场作了LBM编程计算。建立了C语言计算平台，其相对量值分析易达到10-9以上的时空精度， D2G9模型较适合展开声场计算，小周期的速度干扰声压计算与文献结果对比较好。
采用分子动力学的Andresen柔性约束机制，对射流流场这一特定的巨正则系统进行了二维微尺度分子运动仿真研究，各处都表现出湍流的性质，速度脉动呈随机特性。Lagrange密度可以方便的以当地密度和压强进行计算，密度的时间变化近似有二周期特点。与壁面相互作用强烈产生较大的声压，壁面的随机碰撞是一种有效的控制方法。
本文又提出了三势流组合成的复合势流模型，获得了各种声压分布。在点源内部，谐振子作用下的绝对值相比经典情况值较大，中间经历一个虚数“真空带”。双偶极子的内部声压类似于双帽子分布。势流作用下的射流声场，声压在近管口的轴线四周有很强的指向，而管径较大时，整个趋势和示值与文献计算较符合。
本文的研究结果和某些探索，为进一步的声学微观机理研究做了一定铺垫。并为在分子和量子水平上研究宏观气动声场问题，提供了进一步的研究基础和可能的应用技术支持。
Jet aerodynamic noise causes more and more attention. This research aims to studyand analyze the jet aerodynamic sound behavior from macroscopic to microscopic aspects.FEM, FVM, LBM, MDM, and the harmonic oscillator method are adopted respectively,and make some exploration research.
For the non-axisymmetric jet aerodynamic sound field of the confined space withcross flow fan, the rotating jet characteristics and room airflow organization are studiedwith the macro traditional aeroacoustic calculation method. The static pressure spectrumsand power spectral density distributions of the corresponding monitoring points areobtained by numerical analyses and experimental measure, which are induced by flow.
For the axisymmetric rotating jet flow with guide vanes in pipe, the steady-unsteady-LES program is used to study the jet rotation, the pressure spectrum, soundpressure and sound transmission. It is shown that the rotor blades are the main sourcesurface. The Karman vortexes and tip leakage vortexes, passage vortexes from the leadingedge near the wall are the characteristics vortexes. Vortex-sound sources are located in theleading edges and the trailing edges. The turbulent viscosity and effective viscosity of thelateral flow field are larger than that of the middle, as exacerbated the sound of theturbulence dissipation, so sound pressure radiated focus to the environment of the axis.
For the axisymmetric round jet movement, three-dimensional circular nozzle model isobtained with the infinte element method. Three high-Reynolds-number flows and twolow-Reynolds-number flows, with air impedance boundary condition, using Skylinemethod, to describe the acoustic modes corresponding to the flow field, and thecorresponding frequency-domain sound field information. Round jet show that the soundpressure spread with the acoustic impedance characteristic, showing the decoherencemeasurement. The acoustic modes of flow field overlap the nozzle structural modal in thelarge Reynolds number; cross-coupling is not obvious. Sound pressure distributions in thelarge Reynolds number display a weak non-axisymmetric structure, but the sounddistributions with the high Mach number and small Reynolds number in the near-field isspherical characteristic. In the high-frequency part the cone inverse waves from the downstream destroy the wave fronts on both sides of the axis, especially in the upstreamaround the axis.
Micro jet pneumatic sound fields are obtained with the mesoscopic method. The LBMcomputing platform is created by C language. The results show that their relative values canbe more than10-9size accuracy and time price, this greatly improve the accuracy of theCFD simulation. D2G9model is more suited to expand the sound field calculations, thesound pressures with small period radius velocity disturb are better matched with theliterature results.
Two-dimensional microscale grand canonical systems are simulated with Andresenflexible constraint mechanism by molecular dynamics. Throughout the flow field show thenature of the turbulence, and velocity fluctuations is random features. Lagrange density canbe easily calculated in local density and pressure, and there are2-cycle characteristics withthe time-variation of the density approximately. Stronger interaction with the wall producesa larger sound pressure, and so the random collision to the wall is an effective controlmethod.
This paper proposed a composite potential flow model of three potential flows. Withinthe point source, the harmonic oscillator acting sound pressures are larger than the classicsituation, going through an imaginary vacuum belt. Within the dipole source, soundpressure is similar to dual-hat distribution. Under the action of the jet potential flow, soundpressure near the axis of the nozzle bient, there is a strong points, but only in large diametercondition, the whole trend and the values display a good match to the literaturecalculations.
This study results and some exploration pave the way for further acoustic microscopicmechanism; provide a further basis for further study and possible application of technicalsupport for the macro aerodynamic sound field research in molecular and quantum levels.
对于贯流风机非轴对称射流组成的受限空间旋转射流气动声场，本文用宏观传统的气动声学计算方法，研究了它的旋转射流特性及其房间流场的气流组织，数值分析和实验测量了因流动致声的有关对应监测特征点的静压频谱及功率谱密度分布。
对于轴对称管道旋转射流流动，采用定常—非定常—LES的大涡模拟方案，研究了旋转射流特性、压力频谱与声压及其声传播问题。动叶的卡门涡和叶顶泄漏涡，以及叶片前缘产生的近壁叶道涡是动叶组特色涡。涡声的源头位于前缘和尾缘。流场外侧的湍流粘性和有效粘性均大于中部，加剧了声音耗散，声压的幅射重点指向轴线四周。
对于轴对称圆射流运动，本文用有限元方法构造了三维圆喷嘴模型。在射流出口设置空气的阻抗边界条件，用Skyline求解方法，对三种高雷诺数流动和两种低雷诺数流动进行数值分析，用以描述流场对应的声模态和对应频域的声场信息。圆射流的声压是以声阻抗率为特性的传播，呈现测量的退相干性。射流的声模态与管嘴的结构模态在大雷诺数下的高频率段重叠交叉，耦合作用不明显。大雷诺数下的声压指向性呈弱的非轴对称结构，而小雷诺数高马赫数的声压指向在近场是球形的。在高频部分的下游传递出锥状逆波，破坏了轴线两侧的波阵面，尤其是在上游轴线周侧。
本文用介观方法对射流气动声场作了LBM编程计算。建立了C语言计算平台，其相对量值分析易达到10-9以上的时空精度， D2G9模型较适合展开声场计算，小周期的速度干扰声压计算与文献结果对比较好。
采用分子动力学的Andresen柔性约束机制，对射流流场这一特定的巨正则系统进行了二维微尺度分子运动仿真研究，各处都表现出湍流的性质，速度脉动呈随机特性。Lagrange密度可以方便的以当地密度和压强进行计算，密度的时间变化近似有二周期特点。与壁面相互作用强烈产生较大的声压，壁面的随机碰撞是一种有效的控制方法。
本文又提出了三势流组合成的复合势流模型，获得了各种声压分布。在点源内部，谐振子作用下的绝对值相比经典情况值较大，中间经历一个虚数“真空带”。双偶极子的内部声压类似于双帽子分布。势流作用下的射流声场，声压在近管口的轴线四周有很强的指向，而管径较大时，整个趋势和示值与文献计算较符合。
本文的研究结果和某些探索，为进一步的声学微观机理研究做了一定铺垫。并为在分子和量子水平上研究宏观气动声场问题，提供了进一步的研究基础和可能的应用技术支持。
Jet aerodynamic noise causes more and more attention. This research aims to studyand analyze the jet aerodynamic sound behavior from macroscopic to microscopic aspects.FEM, FVM, LBM, MDM, and the harmonic oscillator method are adopted respectively,and make some exploration research.
For the non-axisymmetric jet aerodynamic sound field of the confined space withcross flow fan, the rotating jet characteristics and room airflow organization are studiedwith the macro traditional aeroacoustic calculation method. The static pressure spectrumsand power spectral density distributions of the corresponding monitoring points areobtained by numerical analyses and experimental measure, which are induced by flow.
For the axisymmetric rotating jet flow with guide vanes in pipe, the steady-unsteady-LES program is used to study the jet rotation, the pressure spectrum, soundpressure and sound transmission. It is shown that the rotor blades are the main sourcesurface. The Karman vortexes and tip leakage vortexes, passage vortexes from the leadingedge near the wall are the characteristics vortexes. Vortex-sound sources are located in theleading edges and the trailing edges. The turbulent viscosity and effective viscosity of thelateral flow field are larger than that of the middle, as exacerbated the sound of theturbulence dissipation, so sound pressure radiated focus to the environment of the axis.
For the axisymmetric round jet movement, three-dimensional circular nozzle model isobtained with the infinte element method. Three high-Reynolds-number flows and twolow-Reynolds-number flows, with air impedance boundary condition, using Skylinemethod, to describe the acoustic modes corresponding to the flow field, and thecorresponding frequency-domain sound field information. Round jet show that the soundpressure spread with the acoustic impedance characteristic, showing the decoherencemeasurement. The acoustic modes of flow field overlap the nozzle structural modal in thelarge Reynolds number; cross-coupling is not obvious. Sound pressure distributions in thelarge Reynolds number display a weak non-axisymmetric structure, but the sounddistributions with the high Mach number and small Reynolds number in the near-field isspherical characteristic. In the high-frequency part the cone inverse waves from the downstream destroy the wave fronts on both sides of the axis, especially in the upstreamaround the axis.
Micro jet pneumatic sound fields are obtained with the mesoscopic method. The LBMcomputing platform is created by C language. The results show that their relative values canbe more than10-9size accuracy and time price, this greatly improve the accuracy of theCFD simulation. D2G9model is more suited to expand the sound field calculations, thesound pressures with small period radius velocity disturb are better matched with theliterature results.
Two-dimensional microscale grand canonical systems are simulated with Andresenflexible constraint mechanism by molecular dynamics. Throughout the flow field show thenature of the turbulence, and velocity fluctuations is random features. Lagrange density canbe easily calculated in local density and pressure, and there are2-cycle characteristics withthe time-variation of the density approximately. Stronger interaction with the wall producesa larger sound pressure, and so the random collision to the wall is an effective controlmethod.
This paper proposed a composite potential flow model of three potential flows. Withinthe point source, the harmonic oscillator acting sound pressures are larger than the classicsituation, going through an imaginary vacuum belt. Within the dipole source, soundpressure is similar to dual-hat distribution. Under the action of the jet potential flow, soundpressure near the axis of the nozzle bient, there is a strong points, but only in large diametercondition, the whole trend and the values display a good match to the literaturecalculations.
This study results and some exploration pave the way for further acoustic microscopicmechanism; provide a further basis for further study and possible application of technicalsupport for the macro aerodynamic sound field research in molecular and quantum levels.
引文
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