涡轮叶栅端壁换热特性的数值模拟
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- 英文论文题名：Numerical Simulation of Endwall Heat Transfer in a Turbine Cascade
- 论文作者：张玉芳 ; 郭福水 ; 丁亮
- 英文论文作者：Zhang Yufang ; Guo Fushui ; Ding Liang ; AVIC Commercial Aircraft Engine CO.LTD.
- 年：2016
- 作者机构：中航商用航空发动机有限责任公司;
- 论文关键词：数值模拟 ; 叶栅 ; 端壁 ; 换热特性
- 英文论文关键词：numerical simulation ; cascade ; endwall ; heat transfer
- 会议召开时间：2016-10-31
- 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（下册）
- 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
- 语种：中文
- 分类号：V231.1
- 学会代码：ZGHU
- 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
- 会议地点：中国广东中山
- 主办单位：中国航空学会
- 学会名称：中国航空学会
- 页数：8
- 文件大小：3140k
- 原文格式：O
- 会议级别：全国
摘要
通过RANS数值模拟,对涡轮叶栅端壁附近区域复杂的三维流动和外换热特性进行了兮析。首先选取来自NASA GRC研究中心的跨音速直列叶栅作为验证算例.对比了两种近壁面处理方法(低雷诺数函数法和壁面函数法)和四种湍流模型(标准κ-ε模型、RNGκ-ε模型、κ-ω模型和SST)所得计算结果的精度,结论表明对近壁面使用低雷诺数函数法处理以及使用SST湍流模型时所得计算结果和实验值最接近。在此基础上,采用验证后的计算方法对某高压涡轮一级导叶进行了数值模拟,从结果的分析中可知:入口雷诺数对换热影响非常明显,而出口等熵马赫数的影响较小。
The 3D endwall flow and thermal field in a turbine cascade is studied by using RANS numerical simulation.Firstly,a transonic turbine blade cascade from NASA GRC was used for validation,and the results from two near-wall treatment methods(low-Reynolds number and wall function near-wall treatment) and four turbulence models(standard k- ε,RNG k- ε,k- ωand SST model) were compared with experimental results.It has been concluded that the SST model along with the low-Reynolds number near-wall treatment has prediction superiority among the models examined.Secondly,the validated numerical method was used to simulate the flow and thermal field of a certain high-pressure turbine blade cascade,the results showed that the inlet Reynolds number had an important influence on the enwall heal transfer while the effect of Mach number is little.
The 3D endwall flow and thermal field in a turbine cascade is studied by using RANS numerical simulation.Firstly,a transonic turbine blade cascade from NASA GRC was used for validation,and the results from two near-wall treatment methods(low-Reynolds number and wall function near-wall treatment) and four turbulence models(standard k- ε,RNG k- ε,k- ωand SST model) were compared with experimental results.It has been concluded that the SST model along with the low-Reynolds number near-wall treatment has prediction superiority among the models examined.Secondly,the validated numerical method was used to simulate the flow and thermal field of a certain high-pressure turbine blade cascade,the results showed that the inlet Reynolds number had an important influence on the enwall heal transfer while the effect of Mach number is little.
引文
[1]Ivanov N,Ris V,Smirnov E,Telnov D.Numerical Simulation of Endwall Heat Transfer in a Transonic Turbine Cascade[C].The 12th International Conference on Fluid Flow Technologies,2003.
[2]Levchenya A M,Smirnov E M.Cfd-analysis of 3D Flow Structure and Endwall Heat Transfer in a Transonic Turbine Blade Cascade:Effects of Grid Refinement[C].WestEast High Speed Flow Field Conference,2007.
[3]Luo J,Razinsky E H,Moon H K.3D RANS Prediction of Gas-Side Heat Transfer Coefficients on Turbine Blade and Endwall.ASME Paper GT2011-46723.
[4]Giel P W,Thurman D R,Van Fossen G J,et al.Endwall Heat Transfer Measurements in a Transonic Turbine Cascade[J].Journal of Turbomachinery,1998,120:305-313.
[5]Giel P W,Thurman D R,Boyle R J,et al.ThreeDimensional Flow Field Measurements in a Transonic Turbine Cascade[C].ASME Paper 96-GT-113.
[2]Levchenya A M,Smirnov E M.Cfd-analysis of 3D Flow Structure and Endwall Heat Transfer in a Transonic Turbine Blade Cascade:Effects of Grid Refinement[C].WestEast High Speed Flow Field Conference,2007.
[3]Luo J,Razinsky E H,Moon H K.3D RANS Prediction of Gas-Side Heat Transfer Coefficients on Turbine Blade and Endwall.ASME Paper GT2011-46723.
[4]Giel P W,Thurman D R,Van Fossen G J,et al.Endwall Heat Transfer Measurements in a Transonic Turbine Cascade[J].Journal of Turbomachinery,1998,120:305-313.
[5]Giel P W,Thurman D R,Boyle R J,et al.ThreeDimensional Flow Field Measurements in a Transonic Turbine Cascade[C].ASME Paper 96-GT-113.