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Article(id=1241699538684138073, tenantId=1146029695717560320, journalId=1227999626482147330, issueId=1241699531444769296, articleNumber=null, orderNo=null, doi=10.16579/j.issn.1001.9669.2025.04.017, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=null, receivedDate=1694534400000, receivedDateStr=2023-09-13, revisedDate=1697472000000, revisedDateStr=2023-10-17, acceptedDate=null, acceptedDateStr=null, onlineDate=1773973839684, onlineDateStr=2026-03-20, pubDate=1744646400000, pubDateStr=2025-04-15, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1773973839684, onlineIssueDateStr=2026-03-20, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1773973839684, creator=13701087609, updateTime=1773973839684, updator=13701087609, issue=Issue{id=1241699531444769296, tenantId=1146029695717560320, journalId=1227999626482147330, year='2025', volume='47', issue='4', pageStart='1', pageEnd='157', issueExtLink='null', onlineDate='null', pubDate='null', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=-1, specialIssue=null, createTime=1773973837957, creator=13701087609, updateTime=1773974092709, updator=13701087609, preIssue=null, nextIssue=null, ext={EN=IssueExt(id=1241700600002433947, tenantId=1146029695717560320, journalId=1227999626482147330, issueId=1241699531444769296, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1241700600006628252, tenantId=1146029695717560320, journalId=1227999626482147330, issueId=1241699531444769296, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null}, startPage=139, endPage=147, ext={EN=ArticleExt(id=1241699539309089378, articleId=1241699538684138073, tenantId=1146029695717560320, journalId=1227999626482147330, language=EN, title=Analysis and optimization of heat dissipation of gas mainframe case based on field synergy principle, columnId=1241699532912784251, journalTitle=Journal of Mechanical Strength, columnName=∙Optimization∙Reliability∙, runingTitle=null, highlight=null, articleAbstract=

In order to ensure the safe and stable operation of gas turbine units, and grasp the heat transfer mechanism of the ventilation system of the mainframe housing, a study on the ventilation and heat dissipation of the main engine box of gas turbine units was carried out. Based on the principle of field synergy, the internal flow field, temperature field and heat dissipation performance of key equipments in the mainframe cabinet were analysed, and an optimized scheme for adding a flow-guiding device was proposed. The results show that the volume of the high-temperature area inside the mainframe housing is 7.6%, mainly concentrated near the gas turbine shaft component, which is the main heat source inside the mainframe housing, with an average external surface temperature of 86.94 ℃. After the installation of a 50° flow-guiding device, the volume of the high-temperature area inside the mainframe housing is reduced to 5.1%, and the average external surface temperature of the gas turbine shaft is reduced to 81.98 ℃. The heat dissipation effect is significantly improved.

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HUANG Zhiqiang, E-mail：
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为保证燃气透平机组安全稳定运行，掌握主机箱体通风系统的换热机制，开展了燃气透平机组主机箱体通风散热研究。基于场协同原理，对主机箱体内部流场、温度场和关键设备的散热性能进行分析，并提出加装导流装置的优化方案。结果表明，主机箱体内高温区域体积占比达到7.6%，主要集中在燃气轮机轴部件附近，该部件为主机箱体内主要热源，外表面平均温度高达86.94 ℃；加装50°导流装置后，主机箱体高温区域体积占比减至5.1%，燃气轮机轴外表面平均温度降至81.98 ℃，散热效果得到显著提升。

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黄志强，男，1968年生，四川眉山人，博士，教授；主要研究方向为石油天然气装备等；E-mail：。

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黄志强，男，1968年生，四川眉山人，博士，教授；主要研究方向为石油天然气装备等；E-mail：。

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黄志强，男，1968年生，四川眉山人，博士，教授；主要研究方向为石油天然气装备等；E-mail：。

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caption=Comparison of heat dissipation performance of gas turbine shafts of each scheme, figureFileSmall=xaaUwG3Xl+aNxnj4IHBt+w==, figureFileBig=Mp0ASTNb899YhY+kndjDoA==, tableContent=null), ArticleFig(id=1241699554911899871, tenantId=1146029695717560320, journalId=1227999626482147330, articleId=1241699538684138073, language=CN, label=图13, caption=各方案燃气轮机轴散热性能对比图, figureFileSmall=xaaUwG3Xl+aNxnj4IHBt+w==, figureFileBig=Mp0ASTNb899YhY+kndjDoA==, tableContent=null), ArticleFig(id=1241699555008368869, tenantId=1146029695717560320, journalId=1227999626482147330, articleId=1241699538684138073, language=EN, label=Tab. 1, caption=

Setting of the heat dissipation boundary condition for the rentilation system of the mainframe housing

, figureFileSmall=null, figureFileBig=null, tableContent=
参数类型
Parameter type		具体参数
Specific parameter		边界类型
Boundary type
燃气轮机轴热通量
Gas turbine shaft heat flux q/(W/m³)		4 000体热源
Body heat source
进气蜗壳热通量
Intake worm gear heat flux q/(W/m³)		1 200
太阳辐射的经纬度
Latitude and longitude of solar radiation		E120°N40°太阳辐射模型
Solar radiation model
入口速度
Entrance speed v/ (m/s)		5速度入口
Velocity entrance
入口温度
Entrance temperature Ti/ ℃		40
出口压力
Exit pressure Po/ Pa		101 325压力出口
Pressure exit
), ArticleFig(id=1241699555096449261, tenantId=1146029695717560320, journalId=1227999626482147330, articleId=1241699538684138073, language=CN, label=表1, caption=

主机箱体通风系统散热边界条件设置

, figureFileSmall=null, figureFileBig=null, tableContent=
参数类型
Parameter type		具体参数
Specific parameter		边界类型
Boundary type
燃气轮机轴热通量
Gas turbine shaft heat flux q/(W/m³)		4 000体热源
Body heat source
进气蜗壳热通量
Intake worm gear heat flux q/(W/m³)		1 200
太阳辐射的经纬度
Latitude and longitude of solar radiation		E120°N40°太阳辐射模型
Solar radiation model
入口速度
Entrance speed v/ (m/s)		5速度入口
Velocity entrance
入口温度
Entrance temperature Ti/ ℃		40
出口压力
Exit pressure Po/ Pa		101 325压力出口
Pressure exit
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基于场协同原理的燃气主机箱体散热分析及优化
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黄志强 , 张国旭 , 王智勇 , 王硕 , 王程 , 李涛 , 游正涛
机械强度 | ·优化·可靠性· 2025,47(4): 139-147
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机械强度 | ·优化·可靠性· 2025, 47(4): 139-147
基于场协同原理的燃气主机箱体散热分析及优化
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黄志强 , 张国旭, 王智勇, 王硕, 王程, 李涛, 游正涛
作者信息
  • 西南石油大学 机电工程学院，成都　610500

    • 黄志强，男，1968年生，四川眉山人，博士，教授；主要研究方向为石油天然气装备等；E-mail：。

Analysis and optimization of heat dissipation of gas mainframe case based on field synergy principle
Zhiqiang HUANG , Guoxu ZHANG, Zhiyong WANG, Shuo WANG, Cheng WANG, Tao LI, Zhengtao YOU
Affiliations
  • School of Mechatronic Engineering, Southwest Petroleum University, Chengdu 610500, China
出版时间: 2025-04-15 doi: 10.16579/j.issn.1001.9669.2025.04.017
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摘要
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为保证燃气透平机组安全稳定运行，掌握主机箱体通风系统的换热机制，开展了燃气透平机组主机箱体通风散热研究。基于场协同原理，对主机箱体内部流场、温度场和关键设备的散热性能进行分析，并提出加装导流装置的优化方案。结果表明，主机箱体内高温区域体积占比达到7.6%，主要集中在燃气轮机轴部件附近，该部件为主机箱体内主要热源，外表面平均温度高达86.94 ℃；加装50°导流装置后，主机箱体高温区域体积占比减至5.1%，燃气轮机轴外表面平均温度降至81.98 ℃，散热效果得到显著提升。

燃气透平机组  /  通风散热  /  数值模拟  /  场协同原理  /  优化设计

In order to ensure the safe and stable operation of gas turbine units, and grasp the heat transfer mechanism of the ventilation system of the mainframe housing, a study on the ventilation and heat dissipation of the main engine box of gas turbine units was carried out. Based on the principle of field synergy, the internal flow field, temperature field and heat dissipation performance of key equipments in the mainframe cabinet were analysed, and an optimized scheme for adding a flow-guiding device was proposed. The results show that the volume of the high-temperature area inside the mainframe housing is 7.6%, mainly concentrated near the gas turbine shaft component, which is the main heat source inside the mainframe housing, with an average external surface temperature of 86.94 ℃. After the installation of a 50° flow-guiding device, the volume of the high-temperature area inside the mainframe housing is reduced to 5.1%, and the average external surface temperature of the gas turbine shaft is reduced to 81.98 ℃. The heat dissipation effect is significantly improved.

Gas turbine unit  /  Ventilation and heat dissipation  /  Numerical simulation  /  Field synergy principle  /  Optimization design
黄志强, 张国旭, 王智勇, 王硕, 王程, 李涛, 游正涛. 基于场协同原理的燃气主机箱体散热分析及优化. 机械强度, 2025 , 47 (4) : 139 -147 . DOI: 10.16579/j.issn.1001.9669.2025.04.017
Zhiqiang HUANG, Guoxu ZHANG, Zhiyong WANG, Shuo WANG, Cheng WANG, Tao LI, Zhengtao YOU. Analysis and optimization of heat dissipation of gas mainframe case based on field synergy principle[J]. Journal of Mechanical Strength, 2025 , 47 (4) : 139 -147 . DOI: 10.16579/j.issn.1001.9669.2025.04.017
正文
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0　引言
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主机箱体通风系统是燃气透平机组通风散热的重要部件。夏季高温天气，外界极端温度达到40 ℃，燃气透平机组运行时产生大量热量聚集在主机箱体内部无法排出，整个机组处于“外烤内闷”环境中，导致主机箱体内部温度骤升[1]。若箱体内部长期处于高温状态，燃气轮机轴、进气蜗壳及管线等关键设备温度持续升高易使机组高温报警停机，严重影响透平机组的工作效率与操作人员的安全[2]。
国内外学者对室内环境的通风散热问题进行了诸多研究，研究方向主要集中于通过仿真软件对密闭箱体和工业厂房通风散热问题的模拟分析与优化[3-5]。例如，OU等[6]通过仿真软件研究液化石油气（Liquefied Petroleum Gas, LPG）汽车发动机舱的散热性能，并从温度场和流场相互作用角度阐释发动机舱内局部高温产生的机制，同时提出更改发动机内部部件布局，以提高其散热效果。ZHAN等[7]通过试验研究了封闭腔体内部的散热情况，发现热源数量和间距都会影响腔内流动和传热。张驰宇等[8]通过多场耦合方法研究封闭腔体内器件的散热问题，对比分析了通风口位置和腔体结构对散热效果的影响，提出了在腔体内增加挡板来提高通风散热效率。黄志强等[9]通过试验和仿真研究了页岩气压缩机撬装模块系统的散热性能，并提出了进排风口布局优化方案来提升散热效果。ABANTO等[10]研究了室内多热源情况下的散热效果，并提出热源位置合理布置方法以强化散热。
对流换热是影响设备散热的关键因素。过增元[11]首次提出了场协同原理，通过场协同角评价对流换热的强弱。之后，越来越多的学者使用场协同角研究机械设备的散热问题。LIU等[12]研究了超临界CO2在塔式太阳能接收器中的流动与传热情况，并基于场协同原理设计了三角形肋接收管结构，以增强其对流换热能力。朱兵国等[13]以场协同角为评价指标研究了超临界CO2在渐缩管和渐扩管内的传热特性，并从类冷凝和湍流场分布角度阐释了传热强化的物理机制。
目前，针对海上平台燃气透平机组主机箱体散热问题的研究相对较少，并且少有学者注意大型设备内部高温部件的散热情况。因此，本文采用计算流体动力学（Computational Fluid Dynamics, CFD）方法，研究海上平台QDR20B型燃气透平机组主机箱体内部流场和温度场的分布规律，同时基于场协同原理分析主机箱体内关键设备的散热效果，通过加装导流装置以强化高温部件的对流换热，并对比加装角度下主机箱体内的温度分布和高温部件的场协同角大小，选出最佳角度，为工程设计提供参考。
1　燃气透平机组主机箱体几何结构
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1.1　几何模型
本文研究对象为某2 MW海上平台燃气透平机组，该机组主机箱体通风系统主要由进气系统、主机箱体、排气系统、进气蜗壳及燃气轮机轴等组成，如图1所示。当机组工作时，排气系统内的轴流风机先在主机箱体内产生负压，使冷空气从入口进入主机箱体，并与进气蜗壳和燃气轮机轴等部件进行对流换热，最后通过出口排出主机箱体，从而达到散热效果。
1.2　仿真模型
由于主机箱体内部结构复杂，为了便于仿真，对吊耳、螺孔、螺栓等细微结构进行简化处理，同时抽取主机箱体通风系统内部的流体域与固体域进行共享拓扑，构建仿真计算模型如图2所示。
2　数值模拟
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2.1　控制方程
主机箱体通风系统内部结构复杂，流体处于湍流状态，其流动与换热过程均遵循质量守恒、动量守恒和能量守恒等定律。控制方程表示如下[14]：
1）质量守恒方程为
式中，ρ为流体密度，kg/m3；t为时间，s；ux、uy、uz分别为速度矢量U在x、y、z方向的速度分量，m/s。
2）动量守恒方程为
式中，p为压力，Pa；τ为黏性应力，N；Fx、Fy、Fz为体积力，N。
3）能量守恒方程为
式中，T为热力学温度，K；λ为流体导热系数，W/（m·K）；cp为定压比热容，J/（kg·K）；ST为黏性耗散量，J。
4）燃气透平机组在海上平台工作，太阳辐射较强，因此还需考虑太阳与机组间的辐射换热。太阳可看作黑体，其辐射能力通过斯特藩-玻尔兹曼定律计算[15]，为
式中，j*为单位时间内单位面积辐射出的总能量，J/（s·m2）；ε为黑体的辐射系数，值为1；σ为斯特藩-玻尔兹曼常数，其值约为5.669×10-8 W/（m2·K4）。
2.2　场协同原理
过增元[16]从能量方程出发重新审视了对流换热的物理机制，并在此基础上提出了场协同原理。该原理指出，对流换热强度不仅取决于流体与固体壁面间的温差、流动速度和流体热物理及输运性质，还取决于流体速度矢量与温度梯度的协同程度。场协同角β可以表征速度矢量与温度梯度协同程度，当β<90°时，减小场协同角可以强化传热；当β>90°时，增大场协同角可以提高对流传热效率。其计算式为
式中，Nu为Nusselt数；Re为Reynolds数；Pr为Prandtl数；β为场协同角，（°）；U为速度矢量，m/s；∇T为温度梯度矢量，℃/m。
2.3　边界条件
结合实际情况，主机体通风散热数值模拟需要考虑入口边界、出口边界、燃气轮机轴和进气蜗壳等热源的作用。同时，由于该机组服役于海上平台，夏季高温天气，太阳对机组内部的辐射热不可忽略。因此，依据该机组具体服役地点和高温日照时间，通过Fluent软件中的太阳辐射模型模拟太阳辐射[17]。湍流模型选用标准k-ε湍流模型，流体为不可压缩理想气体。具体的边界条件设置如表1所示。
2.4　网格划分及无关性验证
针对主机箱体通风系统内部结构复杂的特点，选用多面体非结构化网格进行网格划分[18]。由于本文采用流固耦合方法研究主机箱体的温度分布，流固耦合面的计算结果较为重要。因此，在模型固体域和流体域交界面进行局部网格加密，设置5层增长率为1.2的边界层。同时，选取进气蜗壳和燃气轮机轴外表面最高温度为参考值来验证网格无关性，网格数量由104万增加至444万，计算结果如图3所示。当网格数量在151万以上时，进气蜗壳外表面最高温度维持在354 K，最大误差为0.09%；燃气轮机轴外表面最高温度维持在391.5 K，最大误差为0.12%，计算结果趋于稳定。故选用网格数量为151万的多面体非结构网格进行模拟计算。
3　计算结果与分析
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3.1　主机箱体通风系统流场特性分析
3.1.1　整体流场分析
基于主机箱体通风系统内部流场仿真结果，选用箱体内流体平均流速3.53 m/s作为流场高低流速区域分界线，流速在3.53 m/s以上的区域称为高流速区域，流速在3. 53 m/s以下的区域称为低流速区域。
如图4（a）所示，主机箱体通风系统整体流体流速呈“快-慢-快”的趋势，入口和出口处流体流速高，最高流速达9.25 m/s。这是由于主机箱体进排气系统水平段流体流通面积大，竖直段流体流通面积小，使得流体流速大幅增加。而当流体进入主机箱体内，流通面积增大，流速降低。但在进气蜗壳处，流体流通面积减小，导致靠近主机箱壁面附近流体流速大幅增加。在燃气轮机轴部件附近流体流速较低，最低流速为0.67 m/s，流体换热能力较差，易使部件发生高温积聚现象。
如图4（b）所示，主机箱体通风系统内部高流速区域主要分布于进排气系统及箱体两侧壁面，其体积占比仅为33.2%；而低流速区域主要分布在燃气轮机轴附近，其体积占比高达66. 8%。这严重影响了燃气轮机轴部件的散热。
3.1.2　特征截面流场分析
为了准确分析主机箱体通风系统内部的流场特性，从Y、Z方向各选取一个特征截面，如图5所示。
主机箱体进排气系统流场分布较为均匀，但是箱体内部结构复杂，流场分布较为混乱。由图6可知，主机箱体进排气系统流体速度矢量较大，约9 m/s，且流向一致。但在主机箱体内部，由于进气蜗壳和燃气轮机轴体积大，结构复杂，内部流体速度矢量降至约3 m/s，并且在燃气轮机轴附近流体循环流动，形成涡流，不仅无法排出燃气轮机轴产生的热量，还对其不断加热，导致该部件表面温度急剧升高。其涡流分布与汤明玉等[19]研究的燃气轮机箱装体内部涡流分布规律一致。此外，主机箱体内部近壁面处流体速度矢量约5 m/s，但是受涡流影响对内壁面循环加热，导致壁面温度升高。因此，应该对主机箱体内部结构进行优化，减小涡流影响，增强散热。
3.2　主机箱体通风系统温度场特性分析
基于QDR20B型燃气透平机组维护手册，该机组正常运行时，主机箱体通风系统温度设计要求小于或等于60 ℃。以此为依据划分流体温度区间，取60 ℃为分界线，大于60 ℃区域为高温区，小于60 ℃区域为低温区。
由图7可知，主机箱体通风系统的整体散热较差，其温度分布与流场分布相符。并且主机箱体内部壁面温度分布与吴一鸣等[20-21]研究的燃气轮机箱体壁面温度分布规律一致。该机组进排气系统表面温度较低，均在60 ℃以下。燃气轮机轴与进气蜗壳壁面温度较高，其平均温度为86.94 ℃和81. 14 ℃，形成箱体内的高温热源。燃气轮机轴和进气蜗壳交界处温度较高，形成高温区，最高温度达到118. 13 ℃。
同时，受涡流影响高温气体无法及时排出，在主机箱体内循环加热固体壁面，使整个主机箱体内表面平均温度升高至77.76 ℃，不符合其温度设计要求。主机箱内流体高温区域约占整个主机箱体通风系统体积的7.6%，主要集中在燃气轮机轴和进气蜗壳交界处附近，导致该部位热量堆积，易引起机组高温报警停机。因此，需改善主机箱体内高温区的温度分布，保障主机箱体通风系统安全正常运行。
3.3　关键设备散热性能分析
燃气轮机轴是主机箱体通风系统内部主要的高温热源，其温度和对流换热强弱会影响整个系统的散热效果。因此，以主机箱体左侧壁面为基准，每隔280 mm选取特征截面，共选取10个特征截面，研究燃气轮机轴部件的散热性能。截面选取如图8所示。
由图9可知，燃气轮机轴部件散热效果差，外表面温度高，约86.94 ℃。并且越靠近进气蜗壳，燃气轮机轴表面场协同角越小，对流换热能力越强。在截面6和截面9处场协同角分别为79.11°和77.66°，降幅较大。这是因为截面附近流体受涡流影响，速度矢量与温度梯度协同程度增强，场协同角减小。在截面10处，由于流体速度矢量方向变化极快，温度梯度分布不稳定，场协同角增大至81.66°，对流换热减弱。
虽然燃气轮机轴表面对流换热逐渐增强，但是其场协同角依旧比较大，平均场协同角达到80.64°，整体对流换热较弱。并且越靠近进气蜗壳，流体受涡流影响越大，高温流体吸收燃气轮机轴放出的热量后无法及时排出主机箱体，在燃气轮机轴附近循环流动，导致其外表面温度急剧升高。同时，燃气轮机轴附近流体温度也比较高，平均温度达到48.55 ℃，影响整个主机箱体内的散热。因此，需要通过结构优化，减小燃气轮机轴部件表面的场协同角，提高其散热效果。
4　优化设计研究
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4.1　主机箱体散热优化方案设计
根据仿真结果分析可知，燃气轮机主机箱体内高温区域主要集中于燃气轮机轴与进气蜗壳的交界处。该区域附近流体流速低，截面平均场协同角偏大，流体对流换热能力较弱，散热效果差，是主机箱体内部持续高温的主要原因。因此，需要针对该部位进行结构优化设计，以加强其散热效果。
本文研究主机箱通风系统的散热问题，流体与壁面的场协同角均小于90°。依据场协同原理，可以通过减薄热边界层厚度、增加流体扰动和增加壁面上的速度梯度这3种方法减小场协同角，增强壁面与流体间的对流换热[22]。本文提出在主机箱体内进气蜗壳与燃机轮机轴交界处的两侧固体壁面加装导流装置，以增大该区域流体对流换热能力，提高主机箱体内的通风散热效果。以10°为优化区间，分别研究10°、20°、30°、40°、50°、60°、70°这7个角度的导流装置对主机箱体内部通风散热效果的优化情况，其优化方案如图10所示。
4.2　优化方案散热性能对比分析
4.2.1　各方案流场特性对比分析
由图11可知，加装导流装置对主机箱体通风系统内流场影响较小，流体平均流速最大降幅仅为6.9%。并且导流装置角度较小会导致主机箱体通风系统整体流速降低，高流速区体积减小。加装30°导流装置，主机箱体通风系统整体流速较原方案降低3.0%，高流速区体积占比降低1. 7%。这是因为加装导流装置会提高主机箱体内部结构复杂程度，使得流体流动阻力增加，虽然在进气蜗壳处会对流体产生加速效果，但是导流装置角度过低使得流体动能增加量低于流动阻力增加量，导致整体流速降低。
随着导流装置角度增加，主机箱体通风系统整体流速增大，但最高流体平均流速仅为3.55 m/s，较原始方案增幅为0.58%。虽然导流装置角度增大可以增加进气蜗壳附近流体的动能，但是会降低流体流量，导致整体流速增幅较小。比如，加装70°导流装置方案较加装60°导流装置方案，流速增幅仅为0.9%。
4.2.2　各方案温度场特性对比分析
由图12可知，加装导流装置可以降低主机箱体内部部件的表面温度，并且角度越大，燃气轮机轴和进气蜗壳外表面温度降幅越大，但是对箱体内流体温度影响较小。当导流装置角度较小时，主机箱体内流体流速较低，散热效果差，部分部件温度反而会升高。比如，导流装置角度为10°时，进气蜗壳外表面、燃气轮机轴外表面及主机箱体内表面平均温度分别升至81.91、90.17、80.01 ℃，较原始方案增幅分别为0.96%、4.34%和2.90%。
随着导流装置角度增大，主机箱体内流体流速加快，散热效果提高。但是，导流装置角度过大，会在主机箱体内形成涡流，使得空气循环流动，导致主机箱体内表面温度升高。而导流装置角度为50°时，与其他方案相比，进气蜗壳外表面、燃气轮机轴外表面及主机箱体内表面平均温度较低，分别为76.94、81. 98、78. 29 ℃，主机箱体内高温区体积占比最低，仅为5. 1%，散热效果相对较好。
4.2.3　各方案关键设备散热性能对比分析
根据各方案燃气轮机轴散热性能仿真结果，导流装置角度在40°以下时，各方案箱体内部的场协同角平均值在80°以上，因此，以40°为界，40°以下为低角度方案，40°及以上为高角度方案。
图13（a）、图13（b）所示为低角度方案优化后燃气轮机轴各特征截面的温度和场协同角分布，其中黑色曲线表示未加装导流装置的燃气轮机轴各特征截面温度和场协同角分布。由图13（a）、图13（b）可知，低角度方案对燃气轮机轴部件对流换热能力提升较低，燃气轮机轴外表面温度依旧比较高。如加装30°导流装置，燃气轮机轴外表面平均场协同角为79.70°，平均温度约85. 14 ℃。而加装10°导流装置时，燃气轮机轴部件各截面场协同角变化不大，并且导流装置增加了主机箱体内部流场的复杂程度，导致流体流速降低，燃气轮机轴部件表面温度升高至90.17 ℃。在截面9处，由于导流装置改变了流体流向，速度矢量与温度梯度协同程度增强，场协同角减小，对流换热增强，燃气轮机轴表面温度降低。但是，受涡流影响，截面平均场协同角越小，燃气轮机轴外表面平均温度并非越低。如加装30°导流装置方案，截面9平均场协同角最小，为71. 61°，但是燃气轮机轴表面温度却达到94. 05 ℃。同时，加装导流装置使得燃气轮机轴截面4之前区域形成涡流，导致空气循环加热燃气轮机轴，使其外表面平均温度升高。
由图13（c）、图13（d）可知，高角度方案对燃气轮机轴部件散热提升较高，燃气轮机轴外表面平均温度降幅较大。如加装50°导流装置方案，与其他方案相比，燃气轮机轴和进气蜗壳外表面平均温度较低，分别为81.98、76. 94 ℃，且主机箱体内壁面温度最低，为78. 29 ℃。因此，综合主机箱体通风系统整体温度分布，选择50°导流板散热优化效果最佳。
5　结论
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通过数值模拟方法研究海上平台燃气主机箱体通风系统的散热性能，并基于场协同原理，提出在主机箱体内加装导流装置的优化方案。对比加装不同角度导流装置下主机箱体内的散热效果，得出如下结论：
1）燃气透平机组主机箱体通风系统整体散热效果较差。主机箱内流体流速较低，平均流速为3.53 m/s。高温区域体积约占整个主机箱体的7. 6%，燃气轮机轴、进气蜗壳交界及主机箱体内表面平均温度较高，易引起机组报警停机。
2）燃气轮机轴与进气蜗壳为主机箱体内的主要热源。两部件交界处壁面最高温度达118.13 ℃，附近流体最高温度达98. 42 ℃，为主机箱体内的主要高温区。该区域流体流速约3 m/s，部件对流换热能力差，影响主机箱体通风系统整体散热。
3）在主机箱体内进气蜗壳与燃机轮机轴交界处的两侧固体壁面加装导流装置可有效提高主机箱体的通风散热效果。如加装50°导流装置后，主机箱体内低温区域体积占比增至94.9%，燃气轮机轴外表面、进气蜗壳外表面及主机箱体内表面平均温度分别降至81. 98、76. 94、78. 29 ℃。
4）导流装置角度越大，燃气轮机轴部件对流换热越强，但是主机箱体内表面平均温度会升高，因此综合考虑主机箱体通风系统流体平均温度，主机箱体内壁面平均温度及关键设备外表面平均温度，选择50°导流装置为最佳方案。该方案主机箱体通风系统内流体高温区体积占比降幅最大，为35.2%；流体平均温度最低，约46. 16 ℃；整体散热效果较好。
基金
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  • 中海油科技项目(ZX2022ZCZBF6256)
文献
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2025年第47卷第4期
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doi: 10.16579/j.issn.1001.9669.2025.04.017
  • 接收时间：2023-09-13
  • 首发时间：2026-03-20
  • 出版时间：2025-04-15
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  • 收稿日期：2023-09-13
  • 修回日期：2023-10-17
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CNOOC Science and Technology Project(ZX2022ZCZBF6256)
中海油科技项目(ZX2022ZCZBF6256)
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    西南石油大学 机电工程学院，成都　610500
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2种不同金属材料的力学参数
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Family		 属数
Number of
genus		 种数
Number of
species		 占总种数比例
Percentage of
total species (%)		 属
Genus		 种数
Number of
species		 占总种数比例
Percentage of total
species (%)
鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
小菇科 Mycenaceae 2 12 5.74 丝盖伞属 Inocybe 5 2.39
多孔菌科 Polyporaceae 8 14 6.70 蜡蘑属 Laccaria 5 2.39
红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
红菇属 Russula 17 8.13
栓菌属 Trametes 5 2.39
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