低雷诺数下叶片振动对高亚声速压气机附面层流动的影响机制

陈才艳; 张燕峰; 张建设; 张英强; 董旭; 王名杨; 卢新根

doi:10.13224/j.cnki.jasp.20230086

低雷诺数下叶片振动对高亚声速压气机附面层流动的影响机制

doi: 10.13224/j.cnki.jasp.20230086

陈才艳^{1, 2, 3},
张燕峰^{1, 2, 3,*, ,},
张建设^{1, 2, 3},
张英强^{1, 3, 4},
董旭^{1, 3},
王名杨^{1, 3},
卢新根^{1, 2, 3}

1.
中国科学院工程热物理研究所轻型动力重点实验室，北京 100190
2.
中国科学院大学航空宇航学院，北京 100049
3.
中国科学院轻型动力创新研究院北京 100190
4.
华北电力大学能源动力与机械工程学院，北京 102206

基金项目: 国家自然科学基金（52276044）

详细信息

作者简介:
陈才艳（1996-），女，硕士生，主要从事叶轮机械气动热力学研究

通讯作者:
张燕峰（1983-），男，研究员，研究方向为航空发动机气动热力学。E-mail：zhangyf@iet.cn

中图分类号: V232.4
计量
- 文章访问数: 25
- HTML浏览量: 22
- PDF量: 12
- 被引次数: 0
出版历程
- 收稿日期: 2023-02-19
- 网络出版日期: 2024-03-22

Flow loss mechanism of high subsonic compressor blade vibration under low Reynolds number conditions

CHEN Caiyan^{1, 2, 3},
ZHANG Yanfeng^{1, 2, 3,*
, ,},
ZHANG Jianshe^{1, 2, 3},
ZHANG Yingqiang^{1, 3, 4},
DONG Xu^{1, 3},
WANG Mingyang^{1, 3},
LU Xingen^{1, 2, 3}

1.
Key Laboratory of Light-Duty Gas-Turbine，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China
2.
School of Aeronautics and Astronautics，University of Chinese Academy of Sciences，Beijing 100049，China
3.
Innovation Academy for Light-duty Gas Turbine，Chinese Academy of Science，Beijing 100190，China
4.
School of Energy Power and Mechanical Engineering，Power and Mechanical Engineering，North China Electric Power University，Beijing 102206，China

摘要

摘要:
为了探索低雷诺数Re下高亚声速压气机叶片振动对附面层流动状态的影响，利用数值模拟手段分析了压气机叶片在不同振动频率下叶片表面附面层分离、再附及转捩的变化规律和流动损失的变化规律。研究表明，在Re=1.5×10⁵条件下，叶片振动引起附面层垂直壁面法向的相对速度增加，使得分离后的附面层提前与主流发生掺混，促使转捩提前，此时壁面附近法向位置处的法向速度型更饱满，这提升了附面层抗分离的能力，限制了分离泡的发展。此外，叶片振动造成附面层和分离泡厚度变“薄”，这使得尾缘堆积的低能流体减少，削弱了尾缘附近流动堵塞和尾迹掺混，进而减少流动损失，改善了低Re条件下高亚声速压气机叶型的气动性能。
- 低雷诺数 /
- 压气机叶片 /
- 叶片振动 /
- 附面层分离 /
- 转捩
Abstract:
In order to investigate the influence of high subsonic compressor blade vibration on the flow state of the surface layer under low Reynolds number (Re) conditions, numerical simulations were conducted to analyze the rule of separation, re-attachment, transition and flow loss of compressor blade surface boundary layer under different vibration frequencies. According to the simulation results, under the condition of Re=1.5×10⁵, the increase in the normal relative velocity of the vertical wall of the surface layer caused by blade vibration could trigger the mixing of the separated surface layer with the mainstream in advance, which promoted the advance of transition. In this case, the normal velocity pattern at normal position near the wall was fuller, which improved the ability of the boundary layer to resist separation and limited the development of the separation bubble. In addition, the boundary layer and separation bubble thickness became "thin" due to blade vibration, which reduced the accumulation of low-energy fluid at the trailing edge, and weakened flow blockage near the trailing edge and wakes mixing, thereby reducing flow loss and improving the aerodynamic performance of the high subsonic compressor blade under low Re conditions.
- low Reynolds number /
- compressor blade /
- blade vibration /
- boundary layer separation /
- transition

HTML

图 1 V103示意图

Figure 1. Sketch map of V103

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图 2 计算域网格

Figure 2. Computational domain mesh

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图 3 不同网格拓扑的损失系数比较

Figure 3. Comparison of loss coefficients of different grid topology

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图 4 叶片静止时静压分布数值模拟结果与实验结果对比

Figure 4. Comparison of the numerical simulation results and experimental results of the static pressure distribution when the blade is stationary

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图 5 静止和振动时叶片吸力面压力分布

Figure 5. Pressure distribution of blade suction surface at rest and vibration

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图 6 静止与振动叶片吸力面摩擦力对比

Figure 6. Comparison of suction surface friction between stationary and vibrating blades

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图 7 静止和振动叶片吸力面分离泡流线分布

Figure 7. Streamline distribution of suction surface of stationary and vibrating blades

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图 8 静止和振动叶吸力面分离泡流线分布

Figure 8. Streamline distribution of suction surface of stationary and vibrating blades

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图 9 静止与振动叶片吸力面平均速度对比

Figure 9. Comparison of mean velocity on suction surface of stationary and vibrating blade

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图 10 静止和振动叶片吸力面不同流向位置处速度型对比

Figure 10. Comparison of boundary layer velocity at various streamwise locations on the blade suction surface of the stationary and vibrating blade frequencies

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图 11 k₁条件下不同时刻叶片吸力面瞬态速度场及流线分布

Figure 11. Transient velocity field and streamline distribution of blade suction surface at different time under k₁ condition

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图 12 叶片做简谐振动的振动曲线图

Figure 12. Vibration curve of harmonic vibration of blade

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图 13 静态工况与k₁工况（时间平均，瞬时）叶片吸力面转捩位置对比

Figure 13. Comparison of transition position of blade suction surface between static and k₁ working conditions（Time-averaged, Instants in time）

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图 14 静止和不同工况下吸力面间歇系数比较

Figure 14. Comparison of intermittent factor of suction surface at stationary and under different working conditions

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图 15 叶片静止和不同工况下的位移厚度、动量厚度和形状因子比较

Figure 15. Comparison of displacement thickness, momentum thickness and shape factor of blades at stationary and under different working conditions

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图 16 静止和不同工况下尾迹总压分布

Figure 16. Total pressure distribution of wakes at stationary and under different working conditions

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图 17 静止和不同工况下吸力面湍流强度对比

Figure 17. Comparison of suction surface turbulence intensity between stationary and different working conditions

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图 18 不同工况叶片表面分离气泡相对尺寸与总压损失对比

Figure 18. Comparison of the relative size of separation bubbles and total pressure loss on the blade surface under different working conditions

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表 1 V103几何及气动参数

Table 1. V103 Geometric and aerodynamic parameters

参数	数值
C/mm	180
t/s	0.55
$d'_{\mathrm{max}} $/C	0.055
β_u/（°）	48
β_s/（°）	112.5
Ma	0.67
Re	150000
β₁/（°）	132
β₂/（°）	96

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表 2 不同拓扑结构的性能参数对比

Table 2. Comparison of performance parameters of different grid topology

方案	网格数量/10⁵	展向网格层数	单层网格数量/10⁵	总压损失系数ω
0	7.6	2	3.8	0.0499
1	28.6	3	9.53	0.0472
2	33.4	3	11.1	0.0471
3	52.4	4	13.1	0.0470

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表 3 V103工况点参数

Table 3. V103 operating condition point parameters

计算工况参数	数值
进口总压p₀₁/Pa	5090.0
进口总温T₀₁/K	236.1
进口气流角β₁/°	132
进口马赫数Ma	0.67
进口雷诺数Re	150000
进口湍流度T_u	3.5%
出口静压p₂/Pa	4373.76

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表 4 V103不同工况参数

Table 4. V103 parameters under different operating conditions

方案	振动幅度/mm	振动频率/Hz	折合频率
1	0	0	k₀=0
2	0.25%C	1400	k₁=1.275
3	0.25%C	1500	k₂=1.366

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