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涡轮动叶凹槽叶尖流动传热机理及建模研究进展

邹正平,  轩笠铭,  付超

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文章导航 > 航空动力学报  > 2022 >  37(11): 2560-2573
邹正平, 轩笠铭, 付超. 涡轮动叶凹槽叶尖流动传热机理及建模研究进展[J]. 航空动力学报, 2022, 37（11）：2560-2573 doi: 10.13224/j.cnki.jasp.20220207
引用本文: 邹正平, 轩笠铭, 付超. 涡轮动叶凹槽叶尖流动传热机理及建模研究进展[J]. 航空动力学报, 2022, 37（11）：2560-2573 doi: 10.13224/j.cnki.jasp.20220207
shu
ZOU Zhengping, XUAN Liming, FU Chao. Progress on mechanism of flow and heat transfer and modeling of turbine blade squealer tip[J]. Journal of Aerospace Power, 2022, 37（11）：2560-2573 doi: 10.13224/j.cnki.jasp.20220207
Citation: ZOU Zhengping, XUAN Liming, FU Chao. Progress on mechanism of flow and heat transfer and modeling of turbine blade squealer tip[J]. Journal of Aerospace Power, 2022, 37（11）：2560-2573 doi: 10.13224/j.cnki.jasp.20220207
shu

涡轮动叶凹槽叶尖流动传热机理及建模研究进展

doi: 10.13224/j.cnki.jasp.20220207
  • 1.

    北京航空航天大学 航空发动机研究院， 北京 102206

  • 2.

    北京航空航天大学 航空发动机气动热力国家级重点实验室， 北京 102206

  • 3.

    北京航空航天大学 能源与动力工程学院， 北京 102206

基金项目: 国家科技重大专项（J2019-Ⅱ-0012-0032）； 重点实验室基金一般项目（6142702200203）
详细信息
    作者简介:

    邹正平（1970-），男，教授、博士生导师，博士，主要从事高超声速航空发动机、叶轮机气体动力学研究。E-mail：zouzhengping@buaa.edu.cn

  • 中图分类号: V231.3

Progress on mechanism of flow and heat transfer and modeling of turbine blade squealer tip

  • 1.

    Research Institute of Aero-Engine，Beihang University，Beijing 102206，China

  • 2.

    National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics， Beihang University，Beijing 102206，China

  • 3.

    School of Energy and Power Engineering，Beihang University，Beijing 102206，China

    摘要
  • 摘要:

    针对凹槽叶尖流动机理及组织方法，考虑冷却的凹槽叶尖气动与传热特征分析和凹槽叶尖泄漏流动的模化等相关工作的研究进展进行了简要总结。已有的研究表明：凹槽内部的流动对传热有明显的影响；凹槽内的冷却气与泄漏流动存在较强的相互作用，合理的凹槽形状和喷气孔位置可以有效提升叶尖的气动效率并降低热负荷；叶尖的加工和气动参数的不确定性会显著影响凹槽叶尖性能；通过对凹槽内流动结构进行模化，得到的考虑喷气的可压缩条件下的凹槽叶尖性能预测模型经过了实验和数值模拟的结果验证，可以有效评估凹槽叶尖性能，并为工程设计提供参考。

     

    Abstract:

    According to the flow mechanism and organization method of squealer tip, the analysis of aerodynamic and heat transfer characteristics of squealer tip considering cooling, and the modeling of leakage flow of squealer tip were summarized. The results showed that the flow inside the cavity had an obvious effect on the heat transfer. There was a strong interaction between the cooling gas in the cavity and the leakage flow. Reasonable cavity shape and jet hole position can effectively improve the aerodynamic performance and reduce the heat load of the blade tip; The uncertainty of blade tip machining and aerodynamic parameters could significantly affect the performance of squealer tip. By modeling the vortex structure in the cavity, the performance prediction model of the squealer tip considering the compressibility of air jet was verified by experiment and numerical simulation results. The model can effectively evaluate the performance of the squealer tip and provide a reference for engineering design.

     

    • HTML

  • 图 1  不同叶尖间隙条件下端区损失组分占比[19]

    Figure 1.  Proportion of endwall loss components under different tip clearance conditions[19]

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    图 2  平叶尖与吸力侧肋条叶尖流场[27]

    Figure 2.  Flow field of flat tip and suction side squealer tip[27]

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    图 3  不同形式叶尖几何[29]

    Figure 3.  Different configurations of the tip geometry[29]

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    图 4  凹槽内部旋涡结构[24]

    Figure 4.  Vortex structure inside the cavity[24]

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    图 5  凹槽内部旋涡结构示意图[32]

    Figure 5.  Schematic diagram of vortex structure in the cavity[32]

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    图 6  涡轮尖区旋涡结构[33]

    Figure 6.  Vortices flow structure of the turbine blade tip[33]

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    图 7  不同形式压力侧肋条布置方式[37]

    Figure 7.  Different forms of pressure side squealer arrangement [37]

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    图 8  改进的吸力侧肋条示意图[33]

    Figure 8.  Schematic diagram of improved suction side squealer [33]

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    图 9  不同叶尖几何形式叶尖流动状态[32]

    Figure 9.  Tip flow state with different tip geometry[32]

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    图 10  平叶尖与凹槽叶尖泄漏损失系数比较[31]

    Figure 10.  Comparison of leakage loss coefficients of the flat tip and the squealer tip[31]

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    图 11  多尺度流场示意图[43]

    Figure 11.  Schematic diagram of the multi-scale flow field[43]

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    图 12  凹槽叶尖传热系数分布[48]

    Figure 12.  Heat transfer coefficient distribution of the squealer tip[48]

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    图 13  凹槽叶尖叶片吸力侧表面传热系数分布[49]

    Figure 13.  Heat transfer coefficient distribution of the suction blade sucface with a squealer tip[49]

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    图 14  不同肋条高度的凹槽叶尖传热特征[52]

    Figure 14.  Heat transfer characteristics of the squealer tip with different squealer heights[52]

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    图 15  不同轴向位置吸力面叶尖区域传热特征[54]

    Figure 15.  Heat transfer characteristics of suction surface tip region of different axial locations[54]

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    图 16  叶顶气膜冷却条件下凹槽叶尖传热系数分布[58]

    Figure 16.  Heat transfer coefficient distribution of the squealer tip with film cooling in blade tip [58]

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    图 17  凹槽内不同斜向喷气位置对流动结构影响[13]

    Figure 17.  Effect of different oblique jet positions in the cavity on flow structure[13]

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    图 18  不同位置喷气条件下叶尖区域流动结构[64]

    Figure 18.  Flow structure in tip region under different jet locations [64]

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    图 19  凹槽内喷气流线示意图[65]

    Figure 19.  Schematic diagram of jet flow streamline in cavity[65]

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    图 20  冷气源项迭代示意图[67]

    Figure 20.  Schematic diagram of iteration of cooling jet source term[67]

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    图 21  不同计算方法计算结果对比[67]

    Figure 21.  Comparison of calculation results of different calculation methods[67]

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    图 22  吸力侧肋条加厚方案示意图[51]

    Figure 22.  Schematic diagram of suction side squealer thickening[51]

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    图 23  多凹槽叶尖传热系数分布[69]

    Figure 23.  Heat transfer coefficient distribution of squealer tip with multi cavity[69]

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    图 24  彩虹叶顶热负荷及流动状态[71]

    Figure 24.  Heat load and flow state of rainbow squealer tip[71]

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    图 25  凹槽叶尖优化结果[73]

    Figure 25.  Optimization results of squealer tip[73]

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    图 26  有无冷却条件下焊缝对凹槽叶尖热负荷影响[74]

    Figure 26.  Effect of weld on heat load of squealer tip with or without cooling[74]

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    图 27  各参数对凹槽叶尖性能不确定性的影响贡献[78]

    Figure 27.  Contribution of each parameter to the performance uncertainty of the squealer tip[78]

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    图 28  叶尖泄漏流动掺混模型[80]

    Figure 28.  Mixing model of tip leakage flow[80]

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    图 29  凹槽叶尖某喷气截面流动示意图[81]

    Figure 29.  Flow diagram of a squealer tip section with jet[81]

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    图 30  模型预测结果[81]

    Figure 30.  Model prediction results[81]

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    图 31  模型与数值模拟结果对比[33]

    Figure 31.  Comparison between model and CFD result[33]

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    XUAN Liming, ZOU Zhengping, ZENG Fei. Flow analysis and modeling in tip clearance of transonic turbine rotor[EB/OL]. [2022-08-07].https://doi.org/10.13700/j.bh.1001-5965.2021.0635. (in Chinese)
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