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2023 , Vol. 32 >Issue 2: 786 - 799

DOI: https://doi.org/10.1007/s11630-023-1769-z

Numerical Investigation on Flow and Cooling Characteristics of a Micro-Ribbed Vane Endwall

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  • 1. School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China
    2. Yangtze River Delta Research Institute of NPU, Northwestern Polytechnical University, Taicang 215400, China
    3. Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System, Northwestern Polytechnical University, Xi’an 710129, China
    4. NPU-KAI International Joint Laboratory of Advanced Aero-Engine Thermal Structure, Northwestern Polytechnical University, Xi’an 710129, China
    5. AECC Hunan Aviation Powerplant Research Institute, Zhuzhou 412002, China
    6. Department of Energy Sciences, Lund University, Lund SE-22 100, Sweden

网络出版日期: 2023-11-28

基金资助

The authors gratefully acknowledge the support of National Natural Science Foundation of China (No. 52006178), National Key R&D Program of China (No. Y2019-VIII-0007-0168), the Fundamental Research Funds for the Central Universities and the Innovation Capacity Support Plan in Shaanxi Province of China (Grant No. 2023-CX-TD-19), the Swedish Research Council (VR) and the Swedish National Energy Agency (EM).

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Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023
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Numerical Investigation on Flow and Cooling Characteristics of a Micro-Ribbed Vane Endwall

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  • 1. School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China
    2. Yangtze River Delta Research Institute of NPU, Northwestern Polytechnical University, Taicang 215400, China
    3. Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System, Northwestern Polytechnical University, Xi’an 710129, China
    4. NPU-KAI International Joint Laboratory of Advanced Aero-Engine Thermal Structure, Northwestern Polytechnical University, Xi’an 710129, China
    5. AECC Hunan Aviation Powerplant Research Institute, Zhuzhou 412002, China
    6. Department of Energy Sciences, Lund University, Lund SE-22 100, Sweden

Online published: 2023-11-28

Supported by

The authors gratefully acknowledge the support of National Natural Science Foundation of China (No. 52006178), National Key R&D Program of China (No. Y2019-VIII-0007-0168), the Fundamental Research Funds for the Central Universities and the Innovation Capacity Support Plan in Shaanxi Province of China (Grant No. 2023-CX-TD-19), the Swedish Research Council (VR) and the Swedish National Energy Agency (EM).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023
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摘要

叶栅通道内固有压力梯度下产生的二次横流会将冷气射流扫向叶片吸力面侧，导致压力面侧端壁附近的热负荷增强，从而显著影响端壁的气膜冷却效果。因此，本文提出了一种新型的带肋端壁来抑制通道内的横向次流。使用剪切应力传输湍流模型（SST k-ω）求解三维雷诺平均纳维-斯托克斯（RANS）方程的数值模拟研究了质量流量比和肋条布局对端壁表面流动与气膜冷却效果的影响。结果表明，肋条有效抑制了冷却射流从压力面侧朝吸力面侧的迁移效应，增强了冷却射流沿横向的扩散与覆盖，从而显著提高了端壁表面绝热气膜冷却效率。在端壁布置有三条肋且肋的高度等于一倍气膜孔径的情况下，可以获得最高的端壁表面气膜冷却效率。当冷却射流与主流的质量流量比等于0.52%时，带肋端壁的面积平均绝热气膜冷却效率相比平端壁提高了31.6%。此外，由于叶栅通道内部的横向迁移减少，带肋端壁的气动损失相对平端壁也更低。

关键词： vane endwall; micro-ribbed endwall; adiabatic film cooling effectiveness; flow structure; numerical study

本文引用格式

DU Kun, CHEN Qihao, LI Yang, SUNDEN Bengt, LIU Cunliang, LI Wei . Numerical Investigation on Flow and Cooling Characteristics of a Micro-Ribbed Vane Endwall[J]. 热科学学报, 2023 , 32(2) : 786 -799 . DOI: 10.1007/s11630-023-1769-z

Abstract

The secondary flow originated from the inherent pressure gradient inside the vane cascade has a strong impact on the endwall cooling performance as the crossflow sweeps the upstream coolant jet towards the suction side, resulting in intensifying thermal load near the pressure side endwall. Hence a novel ribbed-endwall is introduced to suppress passage crossflow. The effects of the mass flow ratio and the rib layout were examined using numerical simulations by solving the three-dimensional Reynolds-averaged Navier-Stokes (RANS) equations with the shear stress transport (SST) k-ω turbulence model. The results indicate that the ribs effectively prevent the coolant migrating from the pressure side to the suction side, helping the coolant jet to spread along the lateral orientation. Therefore, the endwall adiabatic film cooling effectiveness is substantially improved. The maximum cooling effectiveness is achieved for the case with three-ribs when the height of the rib equals one hole diameter among all cases. The area-averaged adiabatic cooling effectiveness is enhanced by 31.6% relative to the flat endwall when the mass flow ratio of coolant to mainstream equals to 0.52%. More importantly, the ribbed-endwall obtains a relatively lower level of aerodynamic loss owing to the reduced lateral migration inside the vane cascade.

Key words： vane endwall; micro-ribbed endwall; adiabatic film cooling effectiveness; flow structure; numerical study

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