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Article(id=1215700813318640468, tenantId=1146029695717560320, journalId=1210938733613449225, issueId=1215700809971581533, articleNumber=null, orderNo=null, doi=10.19666/j.rlfd.202401013, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=null, receivedDate=1706025600000, receivedDateStr=2024-01-24, revisedDate=null, revisedDateStr=null, acceptedDate=null, acceptedDateStr=null, onlineDate=1767775260524, onlineDateStr=2026-01-07, pubDate=1716566400000, pubDateStr=2024-05-25, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1767775260524, onlineIssueDateStr=2026-01-07, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1767775260524, creator=13701087609, updateTime=1767775260524, updator=13701087609, issue=Issue{id=1215700809971581533, tenantId=1146029695717560320, journalId=1210938733613449225, year='2024', volume='53', issue='5', pageStart='1', pageEnd='148', issueExtLink='null', onlineDate='null', pubDate='null', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=-1, specialIssue=null, createTime=1767775259725, creator=13701087609, updateTime=1767775403954, updator=13701087609, preIssue=null, nextIssue=null, ext={EN=IssueExt(id=1215701414953796264, tenantId=1146029695717560320, journalId=1210938733613449225, issueId=1215700809971581533, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1215701414953796265, tenantId=1146029695717560320, journalId=1210938733613449225, issueId=1215700809971581533, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null}, startPage=101, endPage=108, ext={EN=ArticleExt(id=1215700813649990486, articleId=1215700813318640468, tenantId=1146029695717560320, journalId=1210938733613449225, language=EN, title=Study on film cooling flow characteristics of film holes in rounded corner crater, columnId=1211002405299294959, journalTitle=Thermal Power Generation, columnName=Thermal energy science research, runingTitle=null, highlight=null, articleAbstract=

In order to explore the film cooling potential of crater holes, numerical simulations are performed to investigate the film cooling characteristics of equal-section crater hole, concentric elliptical crater hole, and two types of rounded corner crater holes proposed on the basis of these two types of crater holes. Cooling efficiency curves are analyzed for four types of crater holes at blowing ratios of 0.5, 1.0 and 1.5. The results show that, the crater spreading width of crater holes and crater film holes with rounded corners increases, which is beneficial to spreading coverage of the cooling film. After the crater holes are rounded at three blowing ratios, the Coanda effect strengthenes the ability of the cooling jet to adhere to the wall, and the film cooling efficiency in the near-hole region improves significantly. As the blowing ratio increases, the area-averaged film cooling efficiency after the rounded corner treatment increases by 76%, 139% and 155%, respectively, for the equal-section crater hole. The area-averaged film cooling efficiency improves by 18%, 27%, and 29%, respectively, for the concentric-elliptical crater hole with rounded corner compared with that of the concentric-elliptical crater hole.

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为了挖掘凹坑气膜孔的气膜冷却潜力，数值模拟研究了等截面凹坑孔、同心椭圆凹坑孔以及在这2种孔型基础上提出的2种圆角凹坑气膜孔的气膜冷却特性，对4种凹坑气膜孔在吹风比为0.5、1.0和1.5时的冷却效率曲线进行分析。结果表明：凹坑气膜孔与带圆角凹坑气膜孔的凹坑展向宽度增加，有利于冷却气膜的展向覆盖；在3个吹风比条件下，凹坑气膜孔进行圆角处理之后，附壁效应强化了冷却射流贴附壁面的能力，近孔区域的气膜冷却效率明显提高；随着吹风比增加，对于等截面凹坑孔，圆角处理之后的面平均气膜冷却效率分别提高了76%、139%、155%；圆角同心椭圆凹坑孔相比同心椭圆凹坑孔，面平均气膜冷却效率分别提升18%、27%、29%。

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贺业光（1983），男，高级工程师，主要研究方向为燃气轮机热端部件冷却，。
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张德恒（1998），男，硕士研究生，主要研究方向为燃气轮机热端部件冷却，。

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张德恒（1998），男，硕士研究生，主要研究方向为燃气轮机热端部件冷却，。

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张德恒（1998），男，硕士研究生，主要研究方向为燃气轮机热端部件冷却，。

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tableContent=null), ArticleFig(id=1215700823305277716, tenantId=1146029695717560320, journalId=1210938733613449225, articleId=1215700813318640468, language=EN, label=Tab.1, caption=

Configuration parameters

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项目α/(°)HLab
Case1300.75D4.5D2D1D
Case2300.75D4.5D2D3D
Case3300.75D4.5D2D1D
Case4300.75D4.5D2D3D
), ArticleFig(id=1215700823397552411, tenantId=1146029695717560320, journalId=1210938733613449225, articleId=1215700813318640468, language=CN, label=表1, caption=

孔结构参数

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项目α/(°)HLab
Case1300.75D4.5D2D1D
Case2300.75D4.5D2D3D
Case3300.75D4.5D2D1D
Case4300.75D4.5D2D3D
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圆角凹坑气膜孔的气膜冷却流动特性研究
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张德恒 1 , 贺业光 1, 2 , 杨天华 1 , 张涛 1 , 杜涛 2
热力发电 | 热能科学研究 2024,53(5): 101-108
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热力发电 | 热能科学研究 2024, 53(5): 101-108
圆角凹坑气膜孔的气膜冷却流动特性研究
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张德恒1 , 贺业光1, 2 , 杨天华1, 张涛1, 杜涛2
作者信息
  • 1.沈阳航空航天大学能源与环境学院，辽宁　沈阳　110136
  • 2.东北大学冶金学院，辽宁　沈阳　110819

    • 张德恒（1998），男，硕士研究生，主要研究方向为燃气轮机热端部件冷却，。

通讯作者:

贺业光（1983），男，高级工程师，主要研究方向为燃气轮机热端部件冷却，。
Study on film cooling flow characteristics of film holes in rounded corner crater
Deheng ZHANG1 , Yeguang HE1, 2 , Tianhua YANG1, Tao ZHANG1, Tao DU2
Affiliations
  • 1.College of Energy and Environment, Shenyang Aerospace University, Shenyang 110136, China
  • 2.College of Metallurgy, Northeastern University, Shenyang 110819, China
出版时间: 2024-05-25 doi: 10.19666/j.rlfd.202401013
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摘要
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为了挖掘凹坑气膜孔的气膜冷却潜力，数值模拟研究了等截面凹坑孔、同心椭圆凹坑孔以及在这2种孔型基础上提出的2种圆角凹坑气膜孔的气膜冷却特性，对4种凹坑气膜孔在吹风比为0.5、1.0和1.5时的冷却效率曲线进行分析。结果表明：凹坑气膜孔与带圆角凹坑气膜孔的凹坑展向宽度增加，有利于冷却气膜的展向覆盖；在3个吹风比条件下，凹坑气膜孔进行圆角处理之后，附壁效应强化了冷却射流贴附壁面的能力，近孔区域的气膜冷却效率明显提高；随着吹风比增加，对于等截面凹坑孔，圆角处理之后的面平均气膜冷却效率分别提高了76%、139%、155%；圆角同心椭圆凹坑孔相比同心椭圆凹坑孔，面平均气膜冷却效率分别提升18%、27%、29%。

气膜冷却  /  涡轮叶片  /  圆角凹坑  /  数值模拟  /  肾形涡对

In order to explore the film cooling potential of crater holes, numerical simulations are performed to investigate the film cooling characteristics of equal-section crater hole, concentric elliptical crater hole, and two types of rounded corner crater holes proposed on the basis of these two types of crater holes. Cooling efficiency curves are analyzed for four types of crater holes at blowing ratios of 0.5, 1.0 and 1.5. The results show that, the crater spreading width of crater holes and crater film holes with rounded corners increases, which is beneficial to spreading coverage of the cooling film. After the crater holes are rounded at three blowing ratios, the Coanda effect strengthenes the ability of the cooling jet to adhere to the wall, and the film cooling efficiency in the near-hole region improves significantly. As the blowing ratio increases, the area-averaged film cooling efficiency after the rounded corner treatment increases by 76%, 139% and 155%, respectively, for the equal-section crater hole. The area-averaged film cooling efficiency improves by 18%, 27%, and 29%, respectively, for the concentric-elliptical crater hole with rounded corner compared with that of the concentric-elliptical crater hole.

film cooling  /  turbine blade  /  rounded corner crater  /  numerical simulation  /  counter-rotating vortex pair
张德恒, 贺业光, 杨天华, 张涛, 杜涛. 圆角凹坑气膜孔的气膜冷却流动特性研究. 热力发电, 2024 , 53 (5) : 101 -108 . DOI: 10.19666/j.rlfd.202401013
Deheng ZHANG, Yeguang HE, Tianhua YANG, Tao ZHANG, Tao DU. Study on film cooling flow characteristics of film holes in rounded corner crater[J]. Thermal Power Generation, 2024 , 53 (5) : 101 -108 . DOI: 10.19666/j.rlfd.202401013
正文
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提高燃气轮机做功效率可以有效减少化石燃料的使用，降低二氧化碳排放。近年来，为了提高燃气轮机的循环热效率，涡轮进口温度不断提高，远超涡轮叶片合金材料的熔点。因此必须采用先进的热防护技术[1]。气膜冷却技术是一种非常有效的外部冷却手段，通过在叶片表面形成一层冷却气膜，能够有效地避免叶片与高温燃气直接接触，保护热端部件[2-4]。对于气膜冷却技术，常用的气膜孔型多为圆孔，但冷却射流从圆孔中喷射出来之后，会穿透高温燃气，难以附着在壁面上，导致冷却性能较差[5-6]。因此近几十年来，提高气膜冷却性能在气膜冷却研究领域备受关注。
气膜孔型结构是影响气膜冷却效率大小的主要因素。为了提高气膜冷却效率，国内外研究人员进行了大量的实验与数值模拟研究。Goldstein等人[7]最早研究了气膜孔型结构对气膜冷却性能的影响，并设计了出口扩张孔。研究发现：出口扩张的形式能够降低冷却射流动量，增强冷却射流的贴壁性；同时，产生的展向速度分量使得冷却气膜的展向覆盖明显提高。此后，许多成型气膜孔结构的优化方案被提出[8-13]。Bunker等人[3]对已有的成型气膜孔结构进行了总结，发现成型气膜孔结构相比圆孔能提供更好的气膜冷却效率。但受限制于自身结构过于复杂、加工成本高昂，这些成型气膜孔难以应用于实际。
近年来随着热障涂层技术的发展，热障涂层技术被应用于气膜孔结构改进。Bunker等人[14]首先提出了槽孔的设计，研究发现槽孔在较大的吹风比范围内都能够提供较好的冷却气膜覆盖；并且槽孔可由热障涂层加工制成，易于加工和实际应用。Lu等人[15]在4种吹风比下对槽孔进行了实验研究，并讨论了槽宽与槽深对气膜冷却性能的影响。实验结果表明：槽孔在槽深为0.75D、槽宽为3D（D为气膜孔直径）时具有最佳的冷却性能。Zhang等人[16]对传统横槽、斜面横槽和圆角横槽等槽孔的不同唇形展开了研究。数值计算结果表明，在低吹风比时，唇部结构可以提高槽孔的气膜冷却效果，但在高吹风比时相反。该学者进一步地在叶片模型上提出了一种双曲率槽道气膜冷却孔[17]。数值计算结果表明，在不同吹风比下，双曲率槽道孔的气膜冷却效率均高于传统横槽。这些槽孔改进的本质在于充分利用了附壁效应（coanda effect），使得冷却射流更容易贴附壁面，提高了气膜冷却效率。类似的槽孔改进措施还有锯齿槽孔与双波纹槽孔等[18-19]。此外，凹坑孔结构非常值得关注。这种结构同样可由热障涂层制成。Tran等人[20]研究指出，在槽孔横槽区域中的冷却气体容易被侵入的主流加热而降低冷却效果，同时槽孔连续开槽的设计可能破坏结构的完整性，存在一定的局限性。相比之下，凹坑孔在空间上是离散的，不连续的分布对叶片强度的影响较小。Lu等人[21]在4种吹风比下对槽孔、椭圆凹坑孔和扩张型孔进行了对比分析，结果表明凹坑孔略微提高了气膜冷却效率，但换热系数的显著提高抵消了气膜冷却效率提高所带来的益处。因此研究人员提出了特定形状的凹坑造型来提高气膜冷却效率，例如近壁面流向凹坑孔[22]、心形凹坑孔[23]、椭圆凹坑[24]、三角形凹坑孔[25]等。研究结果表明，这些凹坑造型有效地抑制了肾形涡对的发展，增强了冷却气体在展向方向的扩散，使冷却气体更加贴近冷却壁面，有效提高了气膜冷却效率。
目前，在凹坑孔的气膜冷却特性研究中，主要关注凹坑造型和深度对气膜冷却性能的影响，但很少关注凹坑内壁对气膜冷却性能的影响；同时，提出的新凹坑气膜孔结构大多是通过改变凹坑造型来实现的。为了充分挖掘凹坑孔的气膜冷却潜力，本文提出了一种新造型的圆角凹坑气膜孔结构，并通过数值计算分析了不同吹风比对气膜冷却效率的影响，揭示了圆角凹坑气膜孔的冷却机理。
1　数值方法
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1.1　计算模型
图1中展示了本文研究的4种气膜孔型结构。Case1为等截面椭圆凹坑孔，Case2为同心椭圆凹坑孔，Case3与Case4为这2种凹坑孔基础上设计出的圆角凹坑气膜孔。分别是等截面椭圆凹坑孔、同心椭圆凹坑孔和在这2种凹坑孔基础上设计出的圆角凹坑气膜孔。坐标系原点位于气膜孔出口截面的后缘，X与Y分别代表流向与展向方向。其中D=2 mm，圆角凹坑孔的圆角R=0.5D。详细气膜孔结构参数见表1。
图2为本文数值计算采用的几何模型。计算域模型参考了文献[24]中的设置。主流通道总长70D、高30D，气膜孔与主流通道进口间的距离为15D；冷气腔长25D、高20D；主流通道与冷气腔展向宽度均为6D。需要注意的是，下文中所计算的展向平均气膜冷却效率的计算区域均为−2<Y/D<2。
1.2　边界条件与数值方法
为保证数值计算的准确性，边界条件的设定与湍流模型与文献[24]保持一致。主流入口采用速度进口边界条件，进口速度设定为37 m/s，温度设为363 K，湍流强度设为2.46%。冷却剂入口设定为质量流量边界条件，其大小由吹风比计算得到，温度设为303 K。模拟计算中采用空气作为主流与冷却剂的工质，且为不可压缩理想气体，因此冷却剂与主流空气的密度比约为1.2。主流通道两侧设定为周期性边界条件，主流通道的出口设定为压力出口边界条件，其他边界均设为无滑移绝热壁面条件。采用ANSYS Fluent软件求解计算，湍流模型选择Realizable k-ε模型和增强壁面函数。压力速度耦合采用SIMPLEC算法，所有物理量的离散参数均采用二阶迎风格式。各参数残差小于10–6即认为计算收敛。
吹风比M的定义为：
M=ρcUcρ∞U∞
式中：ρc、ρ∞分别为冷却射流与主流的密度；Uc、U∞分别为冷却射流与主流的速度。
绝热气膜冷却效率η的定义为：
η=T∞−TawT∞−Tc
式中：T∞为主流的温度；Taw为绝热壁温；Tc为冷气腔进口的温度。
无量纲过余温度θ定义为：
θ=T−TcT∞−Tc
式中：T为当地温度。
无量纲涡量强度ωX*定义为：
ωX*=ωXDU∞
式中：ωX为X方向的涡量。
展向平均气膜冷却效率ηave定义为：
ηave=1n∑i=1nηi
式中：ηi为展向第i个节点的气膜冷却效率。
面平均气膜冷却效率ηarea-ave定义为：
ηarea-ave=1A∫ηxydA
式中：ηxy为坐标x、y处微元点的气膜冷却效率。
1.3　网格无关性验证
利用Fluent meshing软件生成多面体非结构化网格，并在冷却壁面和气膜孔区域进行了网格加密处理，设置了15层边界层，增长比设为1.1，保证Z方向第1层网格高度的y+值小于1。图3展示了Case1的计算域网格。
设计了3套不同大小的网格对Case1在吹风比M=0.5下的流向平均气膜冷却效率进行网格无关性验证，结果如图4所示。由图4可见，440万与560万网格计算得到的展向平均气膜冷却效率分布几乎相等。因此本研究中采用440万网格的划分方法。
1.4　数值计算验证
针对文献[24]的DC2模型，在吹风比为1.0时对实验与数值模拟结果进行验证，结果如图5所示。
观察对比结果可知，本文数值计算结果与文献[24]中的结果拟合较好，仅在X/D=0处的误差较大。存在差异的原因推测为：网格生成方法不同所致，文献[24]采用四面体网格划分方法，而本文采用多面体网格划分方法；此外，X/D=0位置在凹坑后缘点，几何模型的特殊导致此处生成的边界层网格差别较大。因此采用相同的湍流模型计算时，在X/D=0处的计算结果误差较大；但在X/D>1时，本文数值计算结果与文献数值计算结果的相对误差小于5%，可以保证本文数值计算结果的准确性。
2　计算结果与讨论
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2.1　气膜冷却效率
图6为4个Case在3种吹风比下的气膜冷却效率云图。其中X/D与Y/D分别代表流向与展向方向的无量纲距离。
在3种吹风比条件下，Case1的冷却气膜覆盖随吹风比增大显著减小，在低吹风比0.5时的冷却气膜覆盖最佳。而Case2中的凹坑展向宽度增加，有利于冷却气体的展向扩散，展向速度分量的产生使得孔下游区域的冷却气膜覆盖明显优于Case1。
在3个吹风比条件下，Case2均提供了较好的冷却性能。随着吹风比增大，Case2中的冷却气膜展向覆盖表现出先增加后减小的趋势，在高吹风比1.5下，冷却气膜展向覆盖面积变小，这是因为高吹风比下冷却空气与主流之间的掺混加剧所致。
对于圆角凹坑气膜孔Case3与Case4，当冷却气体从凹坑出流之后，孔下游区域ΔY范围内均存在比较明显的冷却核心区域（η>0.7）。这是由于附壁效应增强了冷却气体贴近壁面的能力，使得近孔区域的冷却效果增强。随着吹风比增大，Case3与Case4的冷却核心区域面积均表现出先增大后减小的趋势，并且Case3在高吹风比下的冷却核心区域明显变小，而Case4在高吹风比1.5下仍有较好的冷却气膜覆盖。其原因在于：随着吹风比增大，冷却气体动量增强，Case3中的圆角凹坑仅能诱导少量的冷却气体附着在壁面上，大部分的冷却气体与主流发生掺混，导致气膜冷却效率下降；而在Case4中，圆角凹坑展向宽度增加，促进了冷却气体向展向流动，并且可以看到在中高吹风比下，Case4的圆角凹坑内发生了冷却气体回流现象，因此Case4的气膜冷却效率优于Case3。
图7展示了在吹风比为0.5、1.0和1.5时，展向区域（−2<Y/D<2）内所有Case的展向平均气膜冷却效率分布曲线。在3个吹风比条件下，4种模型中Case1的展向平均气膜冷却效率最差，且Case1的气膜冷却性能随吹风比增大而变差，因此在低吹风比0.5时的展向平均气膜冷却效率表现最好。
与Case1相比，Case2同心椭圆凹坑的展向宽度更大，促进了冷却射流在凹坑内部的展向扩散，使得Case2的展向平均气膜冷却效率显著提高，在3个吹风比条件下均提供了较好的冷却效果。
此外，在3种吹风比条件下，Case3相比Case1，Case4相比Case2，凹坑孔圆角处理之后的冷却效果均显著提升。整体来讲，圆角凹坑结构在中高吹风比下对于展向平均气膜冷却效率的提升更显著。在高吹风比1.5时，Case3相比Case1在近孔区域（X/D<5）提高了131%以上，而在距离气膜孔较远的区域（5<X/D<16）提高了近87%；Case4相比Case2在近孔区域（X/D<5）提高了36%以上，而在距离气膜孔较远的区域（5<X/D<16）提高了近26%。需要注意的是，Case2在低吹风比0.5时的展向平均气膜冷却效率与Case3相近，差异较小，而在中高吹风比下，展向平均气膜冷却效率均明显高于Case3。这是因为Case3中，圆角凹坑的存在使得冷却射流在孔下游区域的附着更好，但是在展向方向上，Case2展向扩散冷却射流的能力更强，因此Case2的展向平均气膜冷却效率更高。
图8为3个吹风比条件下，所有Case在指定区域（0<X/D<16，−2<Y/D<2）的面平均气膜冷却效率对比曲线。
随着吹风比增大，Case1与Case3的面平均气膜冷却效率随吹风比增大而减小，而Case2与Case4的面平均气膜冷却效率随吹风比增大表现出先增大后减小的变化趋势。在3种吹风比条件下，Case3的面平均气膜冷却效率相比Case1分别提高了76%、139%、155%，Case4的面平均气膜冷却效率相比Case2分别提高了18%、27%、29%。在所有吹风比条件下，Case4的冷却性能表现最佳。
2.2　流场结构
图9为3个吹风比下X/D=1截面上的无量纲温度与流线分布。由图9可以看到：在Case1的流场中，均由肾形涡对占据主导地位，且随着吹风比增大，肾形涡对的尺寸也随之增大，所以Case1的冷却射流核心高度随吹风比增大而显著增高。在高吹风比1.5时，冷却射流几乎完全脱离冷却壁面，因此在图6中的气膜冷却效率云图中仅在气膜孔下游中心线区域有少量的冷却气膜覆盖。这是因为Case1仅在气膜孔出口略微降低了冷却射流的动量，而没有其他的结构变化，所以Case1的流场结构与圆孔相似。
而Case2中，同心椭圆凹坑的展向宽度变宽，冷却射流在凹坑内先进行展向扩散，而后再溢出凹坑，使得Case2中的无量纲温度分布相比Case1更加均匀，即使在高吹风比下，冷却射流仍较好地附着在冷却壁面上。在高吹风比1.5时，观察到Case2在Y/D=±1.6位置产生了尺寸较小的反肾形涡对，这是因为高吹风比时冷却射流动量较强，部分冷却射流从同心椭圆凹坑两侧溢出导致的。
在Case3与Case4中，圆角凹坑的存在使X/D=1截面中的无量纲温度分布更加均匀，有效地抑制了肾形涡对的不利影响。同时，肾形涡对涡核之间的距离（ΔY）变得更大，有效地减小了肾形涡对抬升冷却射流的不利影响，因此Case3与Case4在X/D=1截面的无量纲温度云图分布更均匀。
图10中展示了吹风比为1.0时，X方向上不同截面的无量纲涡量分布。
由图10可以看出，在X/D=2截面上，Case1流场中的肾形涡对涡量强度最大，抬升冷却射流的能力最强，导致Case1的气膜冷却效率最差。而Case2中，凹坑展向宽度增加，冷却射流展向扩散的同时，也减少了冷却射流与主流的掺混。因此Case2中的肾形涡对涡量强度相比Case1较小，冷却气流更容易附着在壁面上。相较于Case1和Case2，圆角凹坑气膜孔更有效地减小了肾形涡对的涡量强度，并且肾形涡对的涡核更贴近于冷却壁面，气膜冷却效率显著提高。此外还可以看到，凹坑展向宽度增加与凹坑气膜孔圆角处理都能够抑制肾形涡对的涡量强度。相比较而言，凹坑气膜孔圆角处理抑制肾形涡对涡量强度的能力更强。在X/D=5截面上，4个Case流场中的肾形涡对涡量强度均沿着流向方向衰减。相比Case1与Case2，Case3与Case4流场中的肾形涡对几乎消失。这使得圆角凹坑气膜孔的孔下游区域均有较好的冷却气膜覆盖。
图11中展示了吹风比为1.0时Y/D=0中截面的无量纲温度分布。在Case1与Case2中，冷却射流接触凹坑后壁时，并未很好地附着在冷却壁面上。由图11可以看到，黑色虚线处的冷却射流溢出凹坑时，低温冷却射流核心脱离壁面。而圆角凹坑气膜孔Case3与Case4充分利用了附壁效应，冷却射流从凹坑溢出之后，接触到圆角凹坑的圆角时，附壁效应使更多的冷却剂附着在冷却壁面上，并且冷却射流在溢出圆角凹坑之后，冷却射流仍较好地附着在冷却壁面上，保证了冷却射流良好的贴壁性。因此圆角凹坑气膜孔Case3与Case4的冷却气膜覆盖面积相比Case1与Case2明显增大，保证了近孔区域较好的冷却气膜覆盖。
3　结论
收起
1）随吹风比增大，Case1与Case3的气膜冷却效率逐渐减小，而Case2与Case4的气膜冷却效率先增大后减小。
2）凹坑气膜孔的凹坑展向宽度增加，有利于冷却射流展向速度分量的产生，展向冷却气膜覆盖明显提高。
3）凹坑气膜孔圆角处理之后，肾形涡对的涡核间距增大，面平均气膜冷却效率显著提高。在3个吹风比下，Case3相比Case1分别提高76%、139%、155%；Case4相比Case2分别提高18%、27%、29%。
基金
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  • 辽宁省教育厅项目(JYT2020044)
文献
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2024年第53卷第5期
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doi: 10.19666/j.rlfd.202401013
  • 接收时间：2024-01-24
  • 首发时间：2026-01-07
  • 出版时间：2024-05-25
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  • 收稿日期：2024-01-24
基金
Project of Liaoning Provincial Department of Education(JYT2020044)
辽宁省教育厅项目(JYT2020044)
作者信息
    1.沈阳航空航天大学能源与环境学院，辽宁　沈阳　110136
    2.东北大学冶金学院，辽宁　沈阳　110819

通讯作者:

贺业光（1983），男，高级工程师，主要研究方向为燃气轮机热端部件冷却，。
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2种不同金属材料的力学参数
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鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
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红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
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光柄菇属 Pluteus 5 2.39
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