端区边界层扭曲对高负荷涡轮二次流的影响

李六南; 屈骁; 张燕峰; 卢新根; 朱俊强

doi:10.7527/S1000-6893.2025.32394

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DOI: https://doi.org/10.7527/S1000-6893.2025.32394

端区边界层扭曲对高负荷涡轮二次流的影响

李六南 ,
屈骁 ,
张燕峰 ,
卢新根 ,
朱俊强

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1. 北京理工大学
2. 中国科学院工程热物理研究所

收稿日期: 2025-06-09

修回日期: 2025-09-04

网络出版日期: 2025-09-05

基金资助

国家自然科学基金;两机国家科技重大专项;两机国家科技重大专项;轻型涡轮动力全国重点实验室基金

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Effect of Boundary Layer Skew on Secondary Flow in High-Lift Turbine

QU Xiao ,
ZHANG Yan-Feng ,
LU Xin-Gen ,
ZHU Jun-Qiang

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Received date: 2025-06-09

Revised date: 2025-09-04

Online published: 2025-09-05

Supported by

National Natural Science Foundation of China;National Science and Technology Major Project of China;National Science and Technology Major Project of China;National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine

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摘要

转静干涉导致的进口边界层扭曲对高负荷低压涡轮端区二次流的发展具有重要影响。针对民用涡扇发动机高负荷低压涡轮，借助实验和数值模拟相结合的方法，开展了尾迹扫掠下进口边界层扭曲对轮毂端区二次流发展演化的影响机制研究，并量化了上游尾迹、边界层扭曲分别对端区二次流影响的权重占比。结果表明，在进口雷诺数为100,000、湍流度为2.5%的条件下，端区边界层扭曲通过增强端区流体与主流之间的剪切层不稳定性和削弱叶栅通道内的横向压差，减小端区二次流，降低流动损失。随着旋转端壁转速的增加，端区边界层扭曲加剧，这导致了前缘边界层增厚，促进端区二次流发展，增加流动损失。上游尾迹将进一步促进剪切层失稳，使得端区二次流减弱，但尾迹的掺混耗散对低压涡轮整体气动性能带来了负面影响。在栅后0.4 Bx位置处，边界层扭曲使流动损失较基准工况减少3.45%左右，而边界层扭曲的加剧使流动损失增加近6.25%，上游尾迹的掺混耗散使流动损失进一步增加约10.08%。

关键词： 高负荷低压涡轮; 端区二次流; 端区边界层扭曲; 上游尾迹; 非定常流动

本文引用格式

李六南 , 屈骁 , 张燕峰 , 卢新根 , 朱俊强 . 端区边界层扭曲对高负荷涡轮二次流的影响[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.32394

Abstract

The inlet boundary layer skew caused by rotor-stator interaction significantly influences the development of the secondary flow in high-lift low-pressure turbine. For high-lift low-pressure turbines used in civil turbofan engines, the method of combining experi-ment and numerical simulation was employed to investigate the influence mechanisms of inlet boundary layer skew on the develop-ment and evolution of secondary flows under wake sweep. Furthermore, the relative contributions of incoming wakes and boundary layer skew to secondary flow development were systematically quantified. The results indicate that, at an inlet Reynolds number of 100,000 and turbulence intensity of 2.5 %, endwall boundary layer skew reduces secondary flow and flow loss. This occurs by enhancing shear layer instability between the endwall-region fluid and the mainstream, while simultaneously weakening the trans-verse pressure gradient across the cascade channel. Increasing the rotational speed of the rotating endwall intensifies boundary layer skew, leading to thickening of the leading edge boundary layer. This promotes secondary flow development and increases flow loss. Upstream wake further promotes shear layer instability, thereby weakening the secondary flow. However, the mixing dissipation associated with the wake adversely impacts the overall aerodynamic performance of the low-pressure turbine. At the 0.4 Bx position downstream of the cascade, boundary layer skew reduces flow loss by approximately 3.45% compared to the baseline. Conversely, intensification of boundary layer skew increases flow loss by nearly 6.25%. The mixing dissipation from the upstream wake con-tributes a further flow loss increase of about 10.08% relative to the case with intensified skew.

Key words： high-lift low pressure turbine; secondary flow; boundary layer skew; incoming wakes; unsteady flow

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