端壁倒圆对低展弦比超高负荷大折转动叶端区二次流损失影响

马超凡; 隋秀明; 浦健; 赵巍; 裴吉; 赵庆军

doi:10.13224/j.cnki.jasp.20230652

端壁倒圆对低展弦比超高负荷大折转动叶端区二次流损失影响

doi: 10.13224/j.cnki.jasp.20230652

马超凡^{1, 2,},
隋秀明^{2, 3, 4},
浦健^{2, 3},
赵巍^{2, 3, 4},
裴吉¹,
赵庆军^{2, 3, 4, 5,*, ,}

1.
江苏大学流体机械工程技术研究中心，江苏镇江 212000
2.
中国科学院工程热物理研究所，北京 100190
3.
中国科学院工程热物理研究所轻型涡轮动力全国重点实验室，北京 100190
4.
中国科学院大学航空宇航学院，北京 100049
5.
中国科学院工程热物理研究所分布式冷热电联产系统重点实验室，北京 100190

基金项目: 国家科技重大专项（J2019-Ⅱ-0011-0031）；国家自然科学基金（52336002）

详细信息

作者简介:
马超凡（1996-），男，助理工程师，硕士，主要从事叶轮机械气动热力学研究。E-mail：15151838931@163.com

通讯作者:
赵庆军（1977-），男，研究员、博士生导师，博士，主要从事叶轮机械气动热力学研究。E-mail：zhaogingjun@iet.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2023-10-12
- 网络出版日期: 2025-11-26

The impact of end-wall fillet on secondary flow losses in a highly-loaded rotor with low aspect ratio and larger camber angle

MA Chaofan^{1, 2
,},
SUI Xiuming^{2, 3, 4},
PU Jian^{2, 3},
ZHAO Wei^{2, 3, 4},
PEI Ji¹,
ZHAO Qingjun^{2, 3, 4, 5,*
, ,}

1.
Research Center of Fluid Machinery Engineering and Technology，Jiangsu University，Zhenjiang Jiangsu 212000，China
2.
Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China
3.
National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China
4.
School of Areonautics and Astronautics，University of Chinese Academy of Sciences，Beijing 100049，China
5.
Beijing Key Laboratory of Distributed Combined Cooling Heating and Power System，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China

摘要

摘要:
为控制超高负荷大折转动叶二次流损失，借助数值模拟技术分析了转子通道涡、泄漏涡间的演化干涉机制，考察了端壁倒圆对损失的影响，结果表明：动叶前缘至50%轴向弦长，马蹄涡演化形成下通道涡后迅速迁移至近叶顶区域，抑制了上通道涡发展，而上通道涡则减弱了叶顶泄漏涡强度；50%轴向弦长以后，泄漏流与主流剪切效应增强，泄漏涡迅速增强，其与下通道涡共同将上通道涡推离吸力面，使其无法卷吸壁面低能流体，限制了上通道涡发展。在通道涡系卷吸作用下，低能流体在叶顶处堆积，致使叶顶区损失及气流落后角增加，因而端壁二次流诱发的损失是损失的主要来源。倒圆对动叶的影响与传统涡轮存在差别：当倒圆半径小于轮毂前缘边界层厚度，倒圆减弱马蹄涡及下通道涡强度，但增大了端区涡系影响区域，涡系卷吸作用导致吸力面叶根30%～50%弦长范围低能流体减少，径向压力梯度增大，下通道涡径向迁移受限，其对壁面低能流体卷吸量减少，强度减小，涡轮效率因而随倒圆半径增大而增加；当倒圆半径大于轮毂前缘边界层厚度，马蹄涡及下通道涡作用区域减弱，叶根近吸力面低能流体堆积增加，径向压力梯度减小，下通道涡强度及其径向迁移位置、吸力面上堆积的低能流体量增加，因而涡轮效率随倒圆半径增加而降低。
- 低展弦比 /
- 大折转 /
- 高负荷 /
- 端区二次流 /
- 流动控制 /
- 端壁倒圆
Abstract:
The interference mechanisms between the rotor passage vortex and tip leakage vortex were analyzed numerically to control the secondary flow losses in a highly loaded rotor with a low aspect ratio and large camber angle. The impact of end-wall fillets on these losses was also investigated. The results revealed that, at the leading edge up to 50% axial chord length, after the horseshoe vortex was evolved and formed into the hub passage vortex, it quickly moved to the upper part of the blade, limiting the development of the shroud passage vortex and reducing the vorticity of the tip leakage vortex. After 50% axial chord length, the high-speed shear effects between the leakage flow and the mainstream were intensified, rapidly strengthening the tip leakage vortex. The shroud passage vortex was pushed away from the suction surface by the combined action of the hub passage vortex and tip leakage vortex, which prevented it from sucking low-energy fluid onto the suction surface and restricted its growth. Due to the entrainment effect of the passage vortex system, low-energy fluid was accumulated at the blade tip, increasing the flow losses and deviation angles there. As a result, the main cause of losses was attributed to the secondary flow caused by the end-wall. The effect of end-wall fillet on the highly loaded rotor with a low aspect ratio and large camber angle was significantly different from the traditional turbines. When the fillet radius was smaller than the boundary layer thickness at the leading edge of the hub, the fillet could weaken the strength of the horseshoe vortex and the hub passage vortex, but it could increase their influential region. This intensified the entrainment effect of the vortex system, reduced the accumulation of low-energy fluid within the 30%—50% axial chord length range on the suction surface, and increased the radial pressure gradient. Therefore, as the radial migration of the hub passage vortex decreased, its entrainment of low-energy fluid on the suction surface was reduced, resulting in reduced vorticity. When the fillet radius was larger than the boundary layer thickness at the leading edge of the hub, the fillet could weaken the effect region of the horseshoe vortex and the hub passage vortex, increasing the accumulation of low-energy fluid on the suction surface close to the blade root and decreasing the radial pressure gradient. Then the radial migration position and vorticity of the hub passage vortex increased, and low-energy fluid was accumulated on the suction surface. Consequently, turbine efficiency decreased as the fillet radius increased.
- low aspect ratio /
- large camber angle /
- high load /
- end-wall secondary flow /
- flow control /
- end-wall fillet

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图 1 试验与数值计算结果对比

Figure 1. Comparison of experimental result and computation result

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图 2 随网格数变化的效率变化率

Figure 2. Change of efficiency with different mesh number

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图 3 涡轮网格分布

Figure 3. Turbine mesh distribution

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图 4 轮毂和机匣端壁极限流线图

Figure 4. Hub and shroud limiting streamlines pattern

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图 5 转子叶表极限流线图

Figure 5. Limiting streamlines pattern on the rotor blade surface

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图 6 40%轴向截面静压的径向分布

Figure 6. Distribution of static pressure radial at 40% axial

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图 7 轮毂流线图

Figure 7. Hub surface limiting streamline pattern

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图 8 叶顶流线图

Figure 8. Flow streamlines pattern of the shroud

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图 9 叶顶相对马赫数分布云图

Figure 9. Distribution of relative mach number pattern at the tip

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图 10 转子端区轴向涡量及二次流速度矢量分布

Figure 10. Distribution of axial vorticity and Secondary velocity vectors at rotor

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图 11 转子端区相对总压恢复系数分布

Figure 11. Distribution of relative total pressure coefficient at rotor

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图 12 转子尾缘105%相对轴向位置的相对气流角径向分布

Figure 12. Radial distribution of relative flow angle at 105% axial location relative to rotor trailing edge

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图 13 转子不同倒圆半径结构示意图

Figure 13. Schematic diagram of rotor structures with different fillet radii

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图 14 带倒圆动叶的几何模型

Figure 14. Geometry model of rotor with fillet

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图 15 随倒圆半径变化的涡轮效率变化率

Figure 15. Change of efficiency with different fillets

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图 16 随倒圆半径变化的涡轮出口流量变化率

Figure 16. Change of outlet mass flow with different fillets

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图 17 转子尾缘相对总压恢复系数的径向分布

Figure 17. Radial distribution of relative total pressure recovery coefficient at the rotor trailing edge

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图 18 不同倒圆半径动叶前缘的速度分布

Figure 18. Distribution of velocity at the leading of the blade with different fillets

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图 19 不同倒圆半径动叶前缘的涡量分布

Figure 19. Distribution of vorticity at the leading of the blade with different fillets

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图 20 端区40%轴向位置截面的速度径向分布

Figure 20. Radial distribution of velocity at the 40% relative axial chord location in the end-wall region

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图 21 端区40%轴向位置截面的静压系数径向分布

Figure 21. Radial distribution of static pressure coefficient at the 40% axial chord location in the end-wall region

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图 22 不同倒圆半径下端区二次流涡量云图

Figure 22. Vorticity contour plots of end-wall secondary flow under different fillet radii

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图 23 小半径倒圆对不同展弦比动叶涡轮效率的影响

Figure 23. Effect of small radius fillet on the efficiency of turbines with different aspect ratios of rotor

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表 1 叶片主要设计参数

Table 1. Main design parameters of blade

参数导叶动叶

叶片数 38 49

叶高/mm 12.3 12.7

展弦比 0.42 0.44

折转角/（°） 77.8 145.03

级负荷 4.4

流量系数 0.66

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