低雷诺数下低压涡轮叶片振动对分离及转捩的影响机制

张英强; 张燕峰; 朱淼怡; 董旭; 王名扬; 卢新根

doi:10.13224/j.cnki.jasp.20220631

低雷诺数下低压涡轮叶片振动对分离及转捩的影响机制

doi: 10.13224/j.cnki.jasp.20220631

张英强^{1, 2},
张燕峰^{2, 3,*, ,},
朱淼怡^{1, 2},
董旭²,
王名扬²,
卢新根^{2, 3}

1.
华北电力大学能源动力与机械工程学院，北京 102206
2.
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
3.
中国科学院大学，北京 100049

基金项目: 国家自然科学基金（52276044）

详细信息

作者简介:
张英强（1998-），男，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，博士，研究领域为叶轮机械气动热力学。E-mail：zhangyf@iet.cn

中图分类号: V232.4
计量
- 文章访问数: 38
- HTML浏览量: 18
- PDF量: 12
- 被引次数: 0
出版历程
- 收稿日期: 2022-08-29
- 网络出版日期: 2024-03-04

Influence mechanism of low-pressure turbine blade vibration on separation and transition at low Reynolds number

ZHANG Yingqiang^{1, 2},
ZHANG Yanfeng^{2, 3,*
, ,},
ZHU Miaoyi^{1, 2},
DONG Xu²,
WANG Mingyang²,
LU Xingen^{2, 3}

1.
School of Energy，Power and Mechanical Engineering，North China Electric Power University，Beijing 102206，China
2.
Key Laboratory of Light-duty Gas-turbine，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China
3.
University of Chinese Academy of Sciences，Beijing 100049，China

摘要

摘要:
低压涡轮叶片振动显著影响边界层演化过程和流动状态，进而影响气动性能。为了探究低压涡轮叶片振动对分离转捩的影响机制，利用数值模拟手段对比分析了低雷诺数（Re=25000）下低压涡轮叶片不同频率的振动对吸力面边界层分离及转捩和流动损失的影响。研究表明，叶片因振动与流体产生的相对运动使分离流与主流提前相遇从而引发转捩提前，限制分离泡的发展，缩减分离泡的尺寸，削弱分离泡内部回流掺混。叶片振动使边界层厚度有所减小，削弱了尾缘附近的流动阻塞与尾迹掺混，大幅度降低了分离及转捩过程中的湍流脉动水平，上述变化使总压损失得到了大幅度降低，最高可以降低23.02%，气动性能得到大大改善。
- 叶片振动 /
- 低压涡轮叶片 /
- 分离 /
- 转捩 /
- 气动损失
Abstract:
Numerical simulation methods were used to compare and analyze the effects of low-pressure turbine blade vibration at different frequencies on the separation and transition of suction surface boundary layer and flow losses at low Reynolds number (Re=25000), with its aim of exploring the influence mechanism of low-pressure turbine blade vibration on separation and transition. The research showed that the relative motion between the fluid and the blade due to the blade vibration made the separation flow meet the main flow in advance. The advanced transition caused by this was able to limit the development of the separation bubble, reduce the size of the separation bubble and weaken the backflow mixing inside the separation bubble. The blade vibration thinned the boundary layer, weakened the flow blockage and wake mixing near the trailing edge and substantially lowered the turbulent pulsation level in the separation and transition process. Furthermore, the impacts above reduced the total pressure loss up to 23.02%, and improved the aerodynamic performance significantly.
- blade vibration /
- low-pressure turbine blade /
- separation /
- transition /
- aerodynamic loss

HTML

图 1 计算域网格

Figure 1. Computational domain grid

下载: 全尺寸图片幻灯片

图 2 静止叶片静压分布系数数值模拟结果与试验结果对比

Figure 2. Comparison of numerical simulation and experiment results of static pressure distribution coefficient when the blade is stationary

下载: 全尺寸图片幻灯片

图 3 静止和振动叶片吸力面壁面摩擦力对比

Figure 3. Comparison of the friction force on suction surface of stationary and vibrating blades

下载: 全尺寸图片幻灯片

图 4 静止和振动叶片吸力面壁面时均速度对比

Figure 4. Comparison of time-averaged velocities on suction surface of stationary and vibrating blades

下载: 全尺寸图片幻灯片

图 5 静止和振动叶片吸力面不同流向位置处速度型对比

Figure 5. Comparison of boundary layer velocity at various streamwise locations on blade suction surface of stationary and vibrating blades

下载: 全尺寸图片幻灯片

图 6 叶片以175 Hz频率振动时吸力面不同时刻的瞬态压力场及流线分布

Figure 6. Transient pressure field and streamline distribution on suction surface at different times of vibrating blade with 175 Hz

下载: 全尺寸图片幻灯片

图 7 叶片以175 Hz频率振动不同时刻吸力面壁面摩擦力分布

Figure 7. Friction force distribution on suction surface at different times of vibrating blade with 175 Hz

下载: 全尺寸图片幻灯片

图 8 静止和振动叶片吸力面边界层参数对比

Figure 8. Comparison of boundary layer parameters on suction surface of stationary and vibrating blades

下载: 全尺寸图片幻灯片

图 9 静止和振动叶片吸力面湍流度对比

Figure 9. Comparison of turbulence near suction surface of stationary and vibrating blades

下载: 全尺寸图片幻灯片

图 10 静止叶片及不同振动频率叶片叶型损失对比

Figure 10. Comparison of profile losses among stationary blades and blades with different vibration frequencies

下载: 全尺寸图片幻灯片

表 1 叶型PACK-B的几何特性及气动参数

Table 1. Geometric characteristics and aerodynamic parameters of airfoil PACK-B

参数数值

弦长C/mm 83.28
轴向弦长C_ax/mm 75.4
栅距S/mm 66.8
几何进气角β₁/（°） 35
几何出气角β₂/（°） 60
载荷系数 1.1

下载: 导出CSV

参考文献(23)

[1]	ROBERTS W B. The effect of Reynolds number and laminar separation on axial cascade performance[J]. Journal of Engineering for Power,1975,97(2): 261-273. doi: 10.1115/1.3445978
[2]	SUTTON E P,EVANS G P,MCGUINNESS M D,et al. Influence of wall vibrations on a flow with boundary-layer separation at a convex edge[C]//MICHEL R,COUSTEIX J,HOUDEVILLE R. Unsteady turbulent shear flows. Berlin,Germany: Springer,1981: 285-293.
[3]	李虹杨,郑赟. 粗糙度对涡轮叶片流动转捩及传热特性的影响[J]. 北京航空航天大学学报,2016,42(10): 2038-2047. LI Hongyang,ZHENG Yun. Effect of surface roughness on flow transition and heat transfer of turbine blade[J]. Journal of Beijing University of Aeronautics and Astronautics,2016,42(10): 2038-2047. (in Chinese LI Hongyang, ZHENG Yun. Effect of surface roughness on flow transition and heat transfer of turbine blade[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(10): 2038-2047. (in Chinese)
[4]	ABUAF N,BUNKER R S,LEE C P. Effects of surface roughness on heat transfer and aerodynamic performance of turbine airfoils[J]. Journal of Turbomachinery,1998,120(3): 522-529. doi: 10.1115/1.2841749
[5]	孙爽,雷志军,朱俊强,等. 粗糙度对超高负荷低压涡轮边界层影响[J]. 推进技术,2014,35(3): 347-355. SUN Shuang,LEI Zhijun,ZHU Junqiang,et al. Effects of roughness on boundary layer of ultra-high-lift low-pressure turbine[J]. Journal of Propulsion Technology,2014,35(3): 347-355. (in Chinese SUN Shuang, LEI Zhijun, ZHU Junqiang, et al. Effects of roughness on boundary layer of ultra-high-lift low-pressure turbine[J]. Journal of Propulsion Technology, 2014, 35(3): 347-355. (in Chinese)
[6]	MAHALLATI A,MCAULIFFE B R,SJOLANDER S A,et al. Aerodynamics of a low-pressure turbine airfoil at low Reynolds numbers: Part Ⅰ: steady flow measurements[J]. Journal of Turbomachinery,2013,135(1): 011010. doi: 10.1115/1.4006319
[7]	MAHALLATI A,SJOLANDER S A. Aerodynamics of a low-pressure turbine airfoil at low Reynolds numbers: Part Ⅱ: blade-wake interaction[J]. Journal of Turbomachinery,2013,135(1): 011011. doi: 10.1115/1.4006320
[8]	HUANG J. Separation control over low pressure turbine blades using plasma actuators[D]. Notre Dame,US: University of Notre Dame,2005.
[9]	张银波,郑伟. 雷诺数对低压涡轮附面层转捩影响的数值研究[J]. 燃气涡轮试验与研究,2015,28(2): 14-19,40. ZHANG Yinbo,ZHENG Wei. Numerical investigation for the effect of Reynolds number on low pressure turbine transition[J]. Gas Turbine Experiment and Research,2015,28(2): 14-19,40. (in Chinese ZHANG Yinbo, ZHENG Wei. Numerical investigation for the effect of Reynolds number on low pressure turbine transition[J]. Gas Turbine Experiment and Research, 2015, 28(2): 14-19, 40. (in Chinese)
[10]	瞿红春,谭天荣,郭君德,等. 非设计状态下尾迹输运对高负荷低压涡轮附面层的影响[J]. 推进技术,2019,40(9): 1953-1962. QU Hongchun,TAN Tianrong,GUO Junde,et al. Effects of transportation of wakes on boundary layer of high-load low pressure turbine at off-design condition[J]. Journal of Propulsion Technology,2019,40(9): 1953-1962. (in Chinese QU Hongchun, TAN Tianrong, GUO Junde, et al. Effects of transportation of wakes on boundary layer of high-load low pressure turbine at off-design condition[J]. Journal of Propulsion Technology, 2019, 40(9): 1953-1962. (in Chinese)
[11]	梁赟,刘火星,邹正平. 尾迹对低压涡轮边界层稳定性的影响[J]. 航空动力学报,2016,31(4): 886-893. LIANG (Bin\| Yun),LIU Huoxing,ZOU Zhengping. Influence of wakes on boundary layer stability in low-pressure turbines[J]. Journal of Aerospace Power,2016,31(4): 886-893. (in Chinese LIANG (Bin\| Yun), LIU Huoxing, ZOU Zhengping. Influence of wakes on boundary layer stability in low-pressure turbines[J]. Journal of Aerospace Power, 2016, 31(4): 886-893. (in Chinese)
[12]	CUI J,NAGABHUSHANA RAO V,TUCKER P G. Numerical investigation of secondary flows in a high-lift low pressure turbine[J]. International Journal of Heat and Fluid Flow,2017,63: 149-157. doi: 10.1016/j.ijheatfluidflow.2016.05.018
[13]	COULL J D,HODSON H P. Unsteady boundary-layer transition in low-pressure turbines[J]. Journal of Fluid Mechanics,2011,681: 370-410. doi: 10.1017/jfm.2011.204
[14]	SENGUPTA A,TUCKER P. Effects of forced frequency oscillations and free stream turbulence on the separation-induced transition in pressure gradient dominated flows[J]. Physics of Fluids,2020,32(10): 104105. doi: 10.1063/5.0022865
[15]	SENGUPTA A,TUCKER P. Effects of forced frequency oscillations and unsteady wakes on the separation-induced transition in pressure gradient dominated flows[J]. Physics of Fluids,2020,32(9): 094113. doi: 10.1063/5.0023679
[16]	NAKHCHI M E,NAUNG S W,RAHMATI M. DNS of secondary flows over oscillating low-pressure turbine using spectral/hp element method[J]. International Journal of Heat and Fluid Flow,2020,86: 108684. doi: 10.1016/j.ijheatfluidflow.2020.108684
[17]	SCHWARZBACH F,MIMIC D,HERBST F. Profile aerodynamics of an oscillating low-pressure–turbine blade[J]. International Journal of Gas Turbine,Propulsion and Power Systems,2020,11(4): 68-75. doi: 10.38036/jgpp.11.4_68
[18]	MEDIC G,ZHANG V,WANG Guolei,et al. Prediction of transition and losses in compressor cascades using large-eddy simulation[J]. Journal of Turbomachinery,2016,138(12): 121001. doi: 10.1115/1.4033514
[19]	QU Xiao,ZHANG Yanfeng,LU Xingen,et al. Effects of periodic wakes on the endwall secondary flow in high-lift low-pressure turbine cascades at low Reynolds numbers[J]. Proceedings of the Institution of Mechanical Engineers,Part G: Journal of Aerospace Engineering,2019,233(1): 354-368.
[20]	张波,李伟,卢新根,等. 变工况下超高负荷低压涡轮叶片边界层被动控制[J]. 航空动力学报,2012,27(12): 2805-2813. ZHANG Bo,LI Wei,LU Xingen,et al. Ultra-high-lift low-pressure turbine blade boundary layer passive control in different flow conditions[J]. Journal of Aerospace Power,2012,27(12): 2805-2813. (in Chinese ZHANG Bo, LI Wei, LU Xingen, et al. Ultra-high-lift low-pressure turbine blade boundary layer passive control in different flow conditions[J]. Journal of Aerospace Power, 2012, 27(12): 2805-2813. (in Chinese)
[21]	MENTER F. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal,1994,32: 1598-1605. doi: 10.2514/3.12149
[22]	屈骁. 超高负荷低压涡轮端区非定常流动机理及新型调控方法研究[D]. 北京: 中国科学院大学(中国科学院工程热物理研究所),2020. QU Xiao. The investigation of unsteady flow mechanism and new flow control methods in ultra-high-lift LPT cascades[D]. Beijing: Institute of Engineering Thermophysics,Chinese Academy of Sciences,2020. (in Chinese QU Xiao. The investigation of unsteady flow mechanism and new flow control methods in ultra-high-lift LPT cascades[D]. Beijing: Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2020. (in Chinese)
[23]	王名扬,赵胜丰,李紫良,等. 低雷诺数下高亚声速压气机叶型流动损失机理研究[J]. 推进技术,2020,41(5): 1046-1054. WANG Mingyang,ZHAO Shengfeng,LI Ziliang,et al. Flow and loss mechanism of high subsonic compressor airfoil under low Reynolds number conditions[J]. Journal of Propulsion Technology,2020,41(5): 1046-1054. (in Chinese WANG Mingyang, ZHAO Shengfeng, LI Ziliang, et al. Flow and loss mechanism of high subsonic compressor airfoil under low Reynolds number conditions[J]. Journal of Propulsion Technology, 2020, 41(5): 1046-1054. (in Chinese)