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Article(id=1243306167166939392, tenantId=1146029695717560320, journalId=1240685776644648972, issueId=1243306166663622912, articleNumber=null, orderNo=null, doi=10.3969/j.issn.1007-7294.2025.04.014, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=null, receivedDate=1729267200000, receivedDateStr=2024-10-19, revisedDate=null, revisedDateStr=null, acceptedDate=null, acceptedDateStr=null, onlineDate=1774356889764, onlineDateStr=2026-03-24, pubDate=1745078400000, pubDateStr=2025-04-20, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1774356889764, onlineIssueDateStr=2026-03-24, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1774356889764, creator=13701087609, updateTime=1774356889764, updator=13701087609, issue=Issue{id=1243306166663622912, tenantId=1146029695717560320, journalId=1240685776644648972, year='2025', volume='29', issue='4', pageStart='517', pageEnd='679', issueExtLink='null', onlineDate='null', pubDate='null', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=-1, specialIssue=0, createTime=1774356889644, creator=13701087609, updateTime=1774357043129, updator=13701087609, preIssue=null, nextIssue=null, ext={EN=IssueExt(id=1243306810493485479, tenantId=1146029695717560320, journalId=1240685776644648972, issueId=1243306166663622912, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1243306810493485480, tenantId=1146029695717560320, journalId=1240685776644648972, issueId=1243306166663622912, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null}, startPage=669, endPage=679, ext={EN=ArticleExt(id=1243306167406014721, articleId=1243306167166939392, tenantId=1146029695717560320, journalId=1240685776644648972, language=EN, title=Numerical simulation of hydrodynamic and acoustic performance of jet in cross flow, columnId=1241023038381158513, journalTitle=Journal of Ship Mechanics, columnName=Hydro/Structural Acoustics, runingTitle=null, highlight=null, articleAbstract=

The outboard discharge process of an underwater vehicle navigating in water results in an interaction between cross-flow and jet. The fluid dynamic characteristics generated by jet in cross-flow are important topics in the field of fluids. Based on Reynolds average and large eddy simulation method, a numerical calculation model of jet in cross-flow was established in this paper. Then the flow field characteristics of jet in cross-flow were explored in detail. The accuracy of the current method was verified by comparing the results of averaged velocity and fluctuating pressures with those in related references. The velocity and vorticity characteristics of the near-wall surface upstream and downstream of the orifice were investigated based on the results of numerical simulation. Additionally, the characteristics of the sound field in the vicinity of the orifice were analyzed. The results indicate that the impact of jet in cross-flow on the upstream near wall was confined within the range of 6 times the aperture from the orifice. Flow separation occurs in the downstreams of the orifice within a range of 2-14 times the bore size. Under the interaction between the crossflow and the jet flow, the characteristic vortex structure of counter-rotating vortex pairs (CVP) are formed in the downstreams of the orifice. The CVP is formed near the lower edge of the orifice and persists downstream. The vortex core gradually moves away from the wall along the flow distance, and the influence area gradually expands. The primary source of acoustic energy resulting from the interaction between the cross-flow and the jet is situated in close proximity to the wall. The acoustic energy level near the orifice is higher and exhibits a detached characteristic from the wall. Furthermore, the sound pressure level in the downstreams of the orifice is considerably higher than that upstream. The radiation of the sound field is dependent on the direction of flow and exhibits obvious directional characteristics.

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水下航行器舷外排放形成了横流与射流相互作用的流体结构，横流中射流产生的流体动力学特性是流体领域的重要课题。本文基于雷诺平均与大涡模拟方法，建立横流中射流的数值计算模型，将时均速度与脉动压力结果与文献试验结果进行对比，验证计算方法的准确性。基于数值计算结果探究孔口上下游近壁面速度及涡量特性，分析孔口附近的声场特性。结果表明：孔口射流对上游边界层的影响体现在前6倍孔径范围内，孔口下游2~14倍孔径范围内发生流动分离；在横流与射流干涉作用下，孔口下游形成了反对称涡对的特征涡结构；反旋对称涡对形成于孔口下边缘附近，并在下游持续存在，其涡核沿流向距离增加逐渐远离壁面，影响区域逐渐扩大；横流与射流相互作用产生的主要声源位于壁面附近，孔口附近声源水平较高且存在脱离壁面的特征，孔口下游声压水平明显高于孔口上游相同位置，声场辐射与流向相关，存在明显的指向性特征。

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通讯作者，E-mail：
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张博艺（1997-），男，博士研究生

靳国永（1980-），男，博士，教授，通讯作者，E-mail：。

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张博艺（1997-），男，博士研究生

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张博艺（1997-），男，博士研究生

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靳国永（1980-），男，博士，教授，通讯作者，E-mail：。

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靳国永（1980-），男，博士，教授，通讯作者，E-mail：。

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language=CN, orderNo=4, keyword=反旋对称涡对), Keyword(id=1243306181754729131, tenantId=1146029695717560320, journalId=1240685776644648972, articleId=1243306167166939392, language=CN, orderNo=5, keyword=涡声方程)], refs=[Reference(id=1243306187081495392, tenantId=1146029695717560320, journalId=1240685776644648972, articleId=1243306167166939392, doi=null, pmid=null, pmcid=null, year=2019, volume=14, issue=5, pageStart=70, pageEnd=76, url=null, language=null, rfNumber=[1], rfOrder=0, authorNames=陈康, 姚志崇, 周恩东, journalName=中国舰船研究, refType=null, unstructuredReference=陈康，姚志崇，周恩东，等. 基于体积力的海水自流循环系统流速确定方法[J]. 中国舰船研究，2019, 14(5):70-76., articleTitle=基于体积力的海水自流循环系统流速确定方法, refAbstract=null), Reference(id=1243306187152798566, tenantId=1146029695717560320, journalId=1240685776644648972, articleId=1243306167166939392, doi=null, pmid=null, pmcid=null, year=2019, volume=14, issue=5, pageStart=70, pageEnd=76, url=null, language=null, rfNumber=[1], rfOrder=1, authorNames=Chen K, Yao Z C, Zhou E D, 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ArticleFig(id=1243306186506875716, tenantId=1146029695717560320, journalId=1240685776644648972, articleId=1243306167166939392, language=EN, label=Tab.1, caption=

Parameters of boundary layer at 3.6D upstream of orifice

, figureFileSmall=null, figureFileBig=null, tableContent=
边界层参数δ99（mm）δ*（mm）（mm）uτ/u∞
本文结果26.83.82.90.046085
试验结果[17]284.23.10.0366100
), ArticleFig(id=1243306186641093447, tenantId=1146029695717560320, journalId=1240685776644648972, articleId=1243306167166939392, language=CN, label=表1, caption=

孔口上游3.6D边界层参数

, figureFileSmall=null, figureFileBig=null, tableContent=
边界层参数δ99（mm）δ*（mm）（mm）uτ/u∞
本文结果26.83.82.90.046085
试验结果[17]284.23.10.0366100
), ArticleFig(id=1243306186750145357, tenantId=1146029695717560320, journalId=1240685776644648972, articleId=1243306167166939392, language=EN, label=Tab.2, caption=

Comparison of computed and measured results

, figureFileSmall=null, figureFileBig=null, tableContent=
求解方法f1/HzP1/dBf2/HzP2/dB
张楠结果[27]1110.9133.62221.897.1
袁国清结果[26]1180126239190
试验结果[25]1199.5124.32397.588.2
本文方法1188132237995
相对误差*−0.958%6.2%−0.77%7.7%
), ArticleFig(id=1243306186859197269, tenantId=1146029695717560320, journalId=1240685776644648972, articleId=1243306167166939392, language=CN, label=表2, caption=

本文计算结果与试验[1]对比

, figureFileSmall=null, figureFileBig=null, tableContent=
求解方法f1/HzP1/dBf2/HzP2/dB
张楠结果[27]1110.9133.62221.897.1
袁国清结果[26]1180126239190
试验结果[25]1199.5124.32397.588.2
本文方法1188132237995
相对误差*−0.958%6.2%−0.77%7.7%
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横流中射流水动力与声学性能数值模拟研究
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张博艺 , 靳国永 , 叶天贵 , 宋晓济 , 靳淼
船舶力学 | 流体与结构声学 2025,29(4): 669-679
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船舶力学 | 流体与结构声学 2025, 29(4): 669-679
横流中射流水动力与声学性能数值模拟研究
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张博艺, 靳国永 , 叶天贵, 宋晓济, 靳淼
作者信息
  • 哈尔滨工程大学　动力与能源工程学院，哈尔滨　150001

    • 张博艺（1997-），男，博士研究生

    靳国永（1980-），男，博士，教授，通讯作者，E-mail：。

通讯作者:

通讯作者，E-mail：
Numerical simulation of hydrodynamic and acoustic performance of jet in cross flow
Bo-yi ZHANG, Guo-yong JIN , Tian-gui YE, Xiao-ji SONG, Miao JIN
Affiliations
  • College of Energy and Power Engineering, Harbin Engineering University, Harbin 150001, China
出版时间: 2025-04-20 doi: 10.3969/j.issn.1007-7294.2025.04.014
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摘要
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水下航行器舷外排放形成了横流与射流相互作用的流体结构，横流中射流产生的流体动力学特性是流体领域的重要课题。本文基于雷诺平均与大涡模拟方法，建立横流中射流的数值计算模型，将时均速度与脉动压力结果与文献试验结果进行对比，验证计算方法的准确性。基于数值计算结果探究孔口上下游近壁面速度及涡量特性，分析孔口附近的声场特性。结果表明：孔口射流对上游边界层的影响体现在前6倍孔径范围内，孔口下游2~14倍孔径范围内发生流动分离；在横流与射流干涉作用下，孔口下游形成了反对称涡对的特征涡结构；反旋对称涡对形成于孔口下边缘附近，并在下游持续存在，其涡核沿流向距离增加逐渐远离壁面，影响区域逐渐扩大；横流与射流相互作用产生的主要声源位于壁面附近，孔口附近声源水平较高且存在脱离壁面的特征，孔口下游声压水平明显高于孔口上游相同位置，声场辐射与流向相关，存在明显的指向性特征。

射流注入横流  /  边界层特性  /  特征涡结构  /  反旋对称涡对  /  涡声方程

The outboard discharge process of an underwater vehicle navigating in water results in an interaction between cross-flow and jet. The fluid dynamic characteristics generated by jet in cross-flow are important topics in the field of fluids. Based on Reynolds average and large eddy simulation method, a numerical calculation model of jet in cross-flow was established in this paper. Then the flow field characteristics of jet in cross-flow were explored in detail. The accuracy of the current method was verified by comparing the results of averaged velocity and fluctuating pressures with those in related references. The velocity and vorticity characteristics of the near-wall surface upstream and downstream of the orifice were investigated based on the results of numerical simulation. Additionally, the characteristics of the sound field in the vicinity of the orifice were analyzed. The results indicate that the impact of jet in cross-flow on the upstream near wall was confined within the range of 6 times the aperture from the orifice. Flow separation occurs in the downstreams of the orifice within a range of 2-14 times the bore size. Under the interaction between the crossflow and the jet flow, the characteristic vortex structure of counter-rotating vortex pairs (CVP) are formed in the downstreams of the orifice. The CVP is formed near the lower edge of the orifice and persists downstream. The vortex core gradually moves away from the wall along the flow distance, and the influence area gradually expands. The primary source of acoustic energy resulting from the interaction between the cross-flow and the jet is situated in close proximity to the wall. The acoustic energy level near the orifice is higher and exhibits a detached characteristic from the wall. Furthermore, the sound pressure level in the downstreams of the orifice is considerably higher than that upstream. The radiation of the sound field is dependent on the direction of flow and exhibits obvious directional characteristics.

jet in cross-flow  /  boundary layer characteristics  /  vortex structure characteristics  /  counter-rotating vortex pair  /  vortex sound theory
张博艺, 靳国永, 叶天贵, 宋晓济, 靳淼. 横流中射流水动力与声学性能数值模拟研究. 船舶力学, 2025 , 29 (4) : 669 -679 . DOI: 10.3969/j.issn.1007-7294.2025.04.014
Bo-yi ZHANG, Guo-yong JIN, Tian-gui YE, Xiao-ji SONG, Miao JIN. Numerical simulation of hydrodynamic and acoustic performance of jet in cross flow[J]. Journal of Ship Mechanics, 2025 , 29 (4) : 669 -679 . DOI: 10.3969/j.issn.1007-7294.2025.04.014
正文
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0　引言
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水下航行器的自流冷却系统，是一种依靠航行时的动压头实现抽吸海水冷却换热器的节能装置[1-3]，水下航行器行进过程中，自流冷却系统向舷外排放的射流与航行器外部横流相遇，形成射流注入横流的流动现象。射流注入横流又称横流中射流[4-6]（jet in crossflow，简称JICF），是指从喷嘴喷出的射流流体与流经喷嘴出口周围的横流相互作用的流动现象特征，广泛存在于涡轮气膜冷却[7]、海洋工程[8]等领域。
射流注入横流时，两种不同方向及动量的流体相遇碰撞，从而发生强烈的干涉耦合作用，这种相互作用产生了具有大规模旋涡结构的湍流以及不稳定的近壁面速度变化，会引起船体异常振动与声辐射。因此，射流与横流相互作用的流体结构吸引了众多学者的广泛关注。
国内外学者先后通过试验与数值计算等方式，详细研究了横流中射流相关流场的运动特征，学者们大多采用射流与横流的速度比（r=uj/u∞）来描述横流中射流的流场差异。Fric等[9]进行了高流速比下（r>2）流场可视化试验，结果表明孔口下游存在一个类似于卡门涡街的流动结构；Su等[10]通过试验研究了横流中射流后流场速度、涡度及尾迹在近远场的变化特征；Haven等[11]经水洞试验分析了孔口几何形状对JICF近场特性的影响，对射流周围的涡度进行跟踪，确定了孔口形状对新生流向涡的相对贡献。随着研究的深入以及计算流体力学方法的发展，众多学者开始探讨低速比射流入射角、外部激励影响下的射流轨迹与涡结构；Sasongko等[12]探究了声激励对大后倾角射流在横流中的流动特性与混合特性的调制作用；Yuan等[13]采用大涡模拟方法（LES）研究了射流与横流速度比为2和3.3情况下的流动特性，模拟再现了在可视化流动实验中观察到的大规模相干结构，并描述了大规模相干结构与反旋对称涡对（CVP）的形成机制；Chauvat等[14]通过直接数值模拟方法，推导了临界速度比与雷诺数的函数关系，得出了在亚临界速度比下少量噪声会触发发夹涡脱落的结论；国内学者张燕[15]开展了水槽实验并结合数值分析，对横流冲击射流近区流场特征和涡旋结构进行了详细研究；张仪[16]采用数值模拟探究了不同速度比（r）对JICF流动结构的影响。综上所述，可以看出研究人员对JICF的研究，主要集中在速度比对流体结构的影响以及孔口下游尾迹涡量演变规律研究上，而对于孔口上下游近壁面流场特性与声场特性的研究则相对较少。
鉴于前人针对孔口上下游近壁面涡流运动与声场特性之间关联关系研究不足的问题，本文在文献[17]试验模型的基础上开展涡流运动与声场特性分析，旨在探明孔口位置边界层分离以及CVP结构形成过程，并确定主要声源位置，明晰声源辐射特性。本文首先介绍计算方法与模型，然后将数值计算得到的平均项与脉动项结果与相关文献实验进行对比，验证计算结果的准确性。根据计算结果，分析孔口附近壁面法向速度特征以及反对称涡对向下游发展的流动变化，探究横流中射流的主要声源位置与声场辐射特性。最后，总结得出主要结论，以期为射流注入横流干涉特性分析与水下航行器低噪声设计提供参考。
1　计算方法
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1.1　雷诺平均与大涡模拟方法
采用RANS（Reynolds averaged Navier-Stokes equation）方法求解不可压缩流体Navier-Stokes方程，从而计算流场速度及压力的时均项。
流场速度ui可用时均项与脉动项相加表示，
通过对连续性方程与动量方程求雷诺时均，得到时均方程
式中，fi表示统计平均过程，、ρ、μ分别表示流场平均压力、流体密度、流体运动粘度。此时的时均N-S方程并不封闭，基于Boussinesq涡粘性假设，采用不同湍流模型可使方程封闭，本文采用二方程模式的k-ε模型求解雷诺时均项，得到稳定收敛的流场结果后采用大涡模拟进行瞬态计算，瞬态脉动项求解也采用大涡模拟方法。
大涡模拟方法有两个重要的环节：一是滤波，需要将比滤波宽度小的涡滤掉，从而导出描述大涡运动的控制方程；二是建立近似模型来模拟被滤掉的小涡对大涡运动的影响，这可通过在描述大涡运动的控制方程中引入附加应力来实现[18]。其中，划分涡尺度这一过程通过滤波方程来实现，滤波方程可表示为
式中，G（x-x′，∆）为空间滤波函数，它取决于小尺度运动的尺寸和结构；Ω为滤波空间，Δ为滤波宽度，大于Δ尺度的涡将被详细地直接计算。本文采用网格体积滤波，滤波后的连续方程与N-S方程为
式中，为亚格子应力张量，它体现了大尺度量与小尺度量的相互作用。本文采用动态Smagorinsky-Lilly亚网格模型。
1.2　涡声理论与莱特希尔声类比方法
Powell[19]提出的涡声理论建立了涡流运动与声源表征之间的联系，这为分析湍流运动与声场特征提供了思路，Powell的涡声理论由N-S方程重组得出：
式中，ρ、u、p、ω、c分别代表流体密度、速度矢量、流场压力、涡矢量与声速。在低流速下，忽略高阶小量，由式（7）可得：
方程（8）右端表示由速度矢量与涡矢量构成的声源项，其中声源项∇·ρ（ω×u）是低流速流噪声的主要方面，为偶极子源，第二项为四级子源[20]，本文将使用该方程右端项识别JICF流场中主要声源的分布特征。
Lighthill声类比方法[21]是当前计算流噪声的主流方法之一，从连续性方程与动量方程出发，得到Lighthill气动力声基本方程：
式中，Tij=ρvivj + pij-c2ρδij，为Lighthill应力张量，在等熵条件下，p=c2ρ，引入格林函数
考虑存在固体壁面时，基于Curle方程[22]，可得到Lighthill方程的解为
方程右端第一项表示Lighthill应力张量导致的四级子声源，第二项表示流场中固体壁面上脉动压力引起的偶极子声源。
1.3　计算模型与数值方法
本文在Gopalan等[17]试验模型的基础上建立数值模型，数值模型如图1所示，在保持孔口直径、横流截面皆与试验模型相等的基础上，延长了计算域，孔口直径D为9.5 mm，流域总长L=210D，孔口上游长度（本文所有“上游”、“下游”均在流向方向上相对于孔口而言）L1=74D，孔口下游长度L2=136D。展向宽度与垂向高度均为16D，以保证边界层湍流充分发展。x、y、z分别代表流向方向、垂向方向与展向方向。数值模型采用全结构化网格划分方式，基于孔口特征尺寸的网格控制方法，将流向壁面网格尺寸设定在0.38-3.4 mm之间，随流向发展相邻网格尺寸保持1.05倍增长。第一边界层y+=0.4，相邻边界层高度保持1.15倍增长，保证边界层网格到流体网格的平滑过渡，总体网格数量为2756万。边界条件设为速度入口、压力出口以及无滑移壁面边界条件，时间项采用二阶隐式格式离散，动量方程采用限界中心差分格式离散，压力速度耦合采用SIMPLE算法。时间步长为Δt=10−4 s，瞬态数据记录时间超过1.5 s，横流速度u∞为1.96 m/s，速度比r为1，基于射流孔径的横流雷诺数Re=1.85×104。
2　计算方法验证
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基于时均计算得到了孔口上游3.6倍孔径处边界层平均速度，采用运动粘度υ与磨擦速度uτ进行无量纲表示，并与Gopalan等[17]的试验值、Reichardt[23]公式（含粘性底层）估计值与Coles-Hirst[24]公式（不含粘性底层）估计值进行了对比，结果如图2所示。
Coles-Hirst公式（即对数定律）：
Reichardt公式：
式中，u+为无量纲化的时均速度，定义如下：
式中，为平均速度，uτ为磨擦速度，y+为无量纲壁面距离。
由图2可以看出，本文数值模拟结果与上述试验结果以及经验公式估计值吻合良好。孔口上游3.6倍孔径位置处已基本服从壁面定律。表1展示了孔口上游3.6倍孔径位置（x/D=−3.6）的边界层参数结果比较。由表可知，壁面边界层厚度δ99、位移边界层δ*、动量边界层均与试验值[17]吻合较好，两者边界层厚度的差值约为4%。
图3描述了脉动压力自功率谱数值结果与试验结果的对比情况，结果表明，不同位置的脉动项计算结果与试验结果吻合良好。上述边界层平均速度与脉动压力自谱的验证结果，说明数值模拟针对平均项与脉动项的计算结果准确可靠。如此，下面将采用该数值方法，针对时均流场特性与瞬时声场特性展开分析。
3　结果与讨论
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3.1　近壁面时均速度特性分析
由于射流对横流的阻塞效应，孔口附近区域形成了较大的压差。由图4可见，孔口上下游分别形成相对等值的正压区与负压区，而形成的压力梯度主导着孔口附近区域的速度变化及涡流运动。
图5是孔口附近的归一化速度云图，流体在向孔口靠近的过程中，边界层厚度也逐渐增大，孔口上游边界层由外向内逐层被拉伸，形成一个被抬起的速度梯度层，直至孔口上边缘位置，速度梯度层一并被引射到下游。孔口下游近壁面速度变化更为剧烈，产生了影响范围较远的流动分离，横流与射流的干涉作用在孔口下边缘负压区域形成一个包围的速度梯度层，包围区域中心速度为零。孔口上游1-14倍孔径范围内边界层厚度变化如图6所示，随着与孔口距离的减小，边界层厚度逐渐增加。1-2倍孔径边界层厚度为28.9 mm，3-3.6倍孔径具有相同的边界层厚度且低于1倍孔径位置，在6倍孔径之后（x/D<−6）边界层厚度不再变化。
孔口射流导致的流动分离影响范围较远，孔口下游近壁面速度变化特征如图7所示，在孔口下游2-14倍孔径（2<x/D<14）范围内，下游不同位置的速度变化均呈现不同程度的先增加、再衰减、后稳定的过程。孔口下游横流沿负压梯度流动主导了近壁面速度减小的过程，在靠近负压中心位置，速度趋近于0，甚至发生回流。相对而言，越靠近孔口位置，速度变化愈剧烈，但边界层速度能够在更短的壁面距离内达到主流速度并趋于稳定。
3.2　反旋对称涡对的形成过程
反旋对称涡对（CVP）是横流中射流的主要涡流特征，图8（a）-（c）显示了CVP沿流向不同位置的主要形成过程，流向平均涡度的等高线表明了CVP出现的平均位置。在图8（a）中孔口边界形成的轴向涡量向孔口上方脱落，初步形成了位置对等的正负涡度域。在孔口下游1倍孔径位置，来自边界层的流体规律性地卷起从而形成CVP的涡旋中心。随着向下游的发展，CVP的涡核中心逐渐提高，从图8（b）的x/D=1到图8（c）的x/D=4，其在流向上经过了三个孔径距离。同时涡核之间的距离随着流向发展也在增加，最终形成如图8（d）所示的反旋对称涡对的简化模型。如图8（d）和（e）所示，随着CVP向下游发展，其影响区域逐渐扩大。反对称涡对可一直延续至孔口下游20倍孔径位置并继续向下游发展，但涡量衰减明显。可以看到随着向下游流动，边界层附近存在微小涡量，且沿展向增加。
涡流变化导致湍流加剧，湍动能分布特征如图9所示，虚线表示CVP结构平均位置。结合湍流环境分析，湍动能主要分布于孔口中轴线附近区域，而CVP结构占据了湍动能的主要区域，因此CVP结构提供了湍流运动变化的主要贡献。
3.3　横流中射流声场特性分析
涡流运动是流噪声的主要来源，根据式（8）得到了反应涡流运动的涡声声源。在低速流动过程中，忽略高阶小量，涡声声源包含了偶极子与四级子声源。图10展示了由多个瞬态数据平均得到的不同流向位置的涡声声源云图。由图10可知，除孔口壁面外，主要声源分布于垂向壁面附近。如图10（a）所示，孔口下游1倍孔径位置，横流中射流在孔口中轴线附近区域产生了较强的聚集性声源，随着向下游发展，到达孔口下游10倍孔径位置，其中轴线附近区域的声源特征由聚集改为发散，声源强度也同时减小，声源区域扩散至周边，如图10（b）所示。横流中射流沿流向发展的涡声声源特征与CVP的形成过程具有较高的一致性，因此在一定程度上可以认为，CVP主导了非壁面声源的形成与传播。
在进行声场分析之前，有必要对大涡模拟结合Lighthill声类比方法计算流噪声的综合策略进行方法性验证。Lafon等[25]的孔腔绕流试验是水动力噪声领域公认的标杆试验。国内学者袁国清[26]、张楠等[27]均采用此试验数据验证了数值计算方法，并进行了大量的分析与讨论。因此，本文采用此试验数据验证数值计算方法的可靠性。由于相关结果仅用于方法性验证，因此相关数值模型尺寸及边界条件在本文中不再赘述，仅展示计算结果，相关模型参数与边界条件设置请参见文献[26]。
由图11可知，除较低频率（500 Hz以内）计算结果与上述试验存在较大偏差之外，其他频段内均与试验结果吻合良好。特征峰值与特征频率的对比细节如表2所示，f1、f2分别代表图11中出现的两个特征峰值对应的特征频率，P1、P2分别代表图11中的两个线谱特征峰值。由表可见，特征频率的模拟值与试验结果吻合较好，相对偏差保持在1%以内，但对于线谱特征峰值的模拟有一定偏差，但偏差仍保持在7.7%以内。孔腔绕流数值与试验数据对比结果表明，采用LES+Lighthill声类比方法计算流噪声的综合策略可靠性较高，能满足计算要求。
本文基于Lighthill声类比方法得到了横流中射流的声场特性，相关试验的声压数据监测点如图12所示，位于计算域底面流向中心轴线上。孔口上下游附近区域的声压水平随频率变化特征如图13所示，孔口附近区域下游的声压水平明显高于上游相同位置。为探究横流中射流声压水平随位置变化的关系，经线谱声压累加计算得到了总声级随位置变化特征。总声级随孔口距离的变化如图14（a）所示，孔口上游3倍孔径之外的区域已基本趋于稳定，而孔口下游在2倍孔径位置达到峰值后逐渐降低，峰值总声级与上游稳定水平相差20 dB左右，在孔口下游15倍孔径位置尚高出上游稳定水平5 dB左右，因此横流中射流恢复稳定声压水平需要较远的距离。根据上文时均速度特性分析，孔口下游2-14倍孔径处于速度分离区，而分离区的速度波动特性与该区域的高声压水平存在较大关系。图14（b）描述了距离孔口中心半径2D的周向位置的总声级在y=0平面的分布特性，由图14（b）可知，总声级沿展向存在近似对称分布特征，上游为0°，下游为180°，在下游120°范围内（120°-180°，180°-240°）声压水平急剧升高，在150°-210°范围内，总声级保持较高水平，是JICF流场涡流噪声主要的辐射方向。
4　结论
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本文通过雷诺平均与大涡模拟方法研究了横流中射流的近壁面流场特性与声场特性，数值计算时均项及脉动项结果与相关文献试验结果吻合良好，验证了本文计算结果的正确性。基于流场计算结果分析了孔口下游不同位置边界层速度演化机制以及CVP的形成过程。基于涡声理论与lighthill声类比方法，识别了主要声源位置，探究了孔口附近区域声场辐射特性。得到以下主要结论：
（1）孔口上下游分别形成了相对等值的正压区与负压区，孔口上游边界层受压力梯度影响发生变形，随着监测点与孔口位置距离的减小，边界层厚度逐渐增加。孔口下游2-14倍孔径范围内发生流动分离，14倍孔径之后边界层速度逐渐恢复壁面湍流特性。
（2）分离的边界层与孔口结构的相互作用是众多涡度的起源，反旋对称涡对形成于孔口下边缘，在向下游流动过程中反旋对称涡对的涡量逐渐衰减，涡核沿垂向抬升，影响区域逐渐扩大。反旋对称涡对提供了湍流能量的主要贡献。
（3）横流中射流的声场特征沿流向位置变化存在较大差异，孔口上游3倍孔径之外趋于稳定水平，孔口下游2倍孔径位置声压水平达到最大，孔口下游15倍孔径位置仍比上游稳定水平高5 dB左右。声场辐射特性近似展向对称，孔口下游流向与展向夹角为30°的对称区域是横流中射流声场辐射的主要方向。
基金
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  • 国家自然科学基金资助项目(52225109)
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doi: 10.3969/j.issn.1007-7294.2025.04.014
  • 接收时间：2024-10-19
  • 首发时间：2026-03-24
  • 出版时间：2025-04-20
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  • 收稿日期：2024-10-19
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国家自然科学基金资助项目(52225109)
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    哈尔滨工程大学　动力与能源工程学院，哈尔滨　150001

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