端壁SJA对压气机叶栅角区分离影响

郑维新; 曾聪; 陈绍文

doi:10.13224/j.cnki.jasp.20230563

端壁SJA对压气机叶栅角区分离影响

doi: 10.13224/j.cnki.jasp.20230563

郑维新^1,,
曾聪^2,,
陈绍文^2,*, ,

1.
中国联合重型燃气轮机技术有限公司，北京 100016
2.
哈尔滨工业大学能源科学与工程学院，哈尔滨 150001

基金项目: 航空科学基金（2023M039077001）；国家自然科学基金（U2233207）

详细信息

作者简介:
郑维新（1976-），男，高级工程师，主要从事燃气轮机/航空发动机设计研究。E-mail：zhengweixin1976@163.com

通讯作者:
陈绍文（1979-），男，教授，博士生，主要从事叶轮机械设计及流动控制研究。E-mail：cswemail@hit.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2023-09-04
- 网络出版日期: 2024-05-28

Effect of endwall SJA on the corner separation of compressor cascade

ZHENG Weixin^1
,,
ZENG Cong^2
,,
CHEN Shaowen^{2,*
, ,}

1.
China United Heavy Duty Gas Turbine Technology Company Limited, Beijing 100016, China
2.
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要:
针对某型轴流压气机叶栅角区存在流动分离的问题，利用扫频射流激励器（SJA）主动流动控制技术，采用非定常数值计算方法对端壁SJA控制压气机平面叶栅角区分离的影响机理进行研究，分析和讨论了SJA位置布置、射流压比设定、射流偏角设定的影响规律和流场特性。研究结果表明：端壁SJA主要影响端壁和叶片表面附面层的发展和迁移，通过抑制集中脱落涡的生成与发展，以达到抑制角区分离、减小角区流动损失的目的；当SJA布置在轴向位置$ {x}_{\mathrm{S}\mathrm{J}\mathrm{A}} $/b=85%处、靠近吸力面时，降低流动损失的效果最佳；当SJA射流压比大约为1.01时，利用仅占主流0.03%的射流流量就可使得总压损失系数减小13.4%。此外，通过合理设计SJA射流偏角可有效改善端壁SJA存在的“扫掠盲点”问题，使得SJA控制效果得到进一步提高。
- 压气机叶栅 /
- 角区分离 /
- 扫频射流激励器（SJA） /
- 非定常流动控制 /
- 射流位置 /
- 总压损失
Abstract:
To address the issue of flow separation in the corner region of an axial flow compressor, an active flow control technique called sweeping jet actuator (SJA) was employed. Unsteady numerical simulations were conducted to investigate the impact of endwall SJA jets on mitigating flow separation in the compressor’s corner region. The effects of SJA placement, jet pressure ratio, jet skew angle, and their influence on flow characteristics were analyzed and discussed. The results indicated that the endwall SJA jets primarily affected the development and migration of the boundary layer on the endwall and blade surfaces. By suppressing the generation and development of concentrated shedding vortices, the corner separation was suppressed and the flow loss in the corner was reduced. Moreover, the optimal configuration for loss reduction was achieved when the SJA was positioned at approximately$ {x}_{\mathrm{S}\mathrm{J}\mathrm{A}}/b $=85% along the axial direction and close to the suction surface. When the jet pressure ratio for the SJA was approximately 1.01, with the help of only 0.03% of the mainstream flow for the jet flow, a relative reduction of 13.4% in total pressure loss coefficient can be achieved. Furthermore, by appropriately designing the jet skew angle, the issue of “sweeping blind spots” in the endwall SJA can be effectively mitigated, leading to further enhancement of the SJA controlling effectiveness.
- compressor cascade /
- corner separation /
- sweeping jet actuators (SJA) /
- unsteady fow control /
- injection position /
- total pressure loss

HTML

图 1 数值计算模型图

Figure 1. Schematic diagram of the numerical model

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图 2 SJA端壁布置示意图

Figure 2. Schematic diagram of the SJA end wall arrangement

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图 3 网格划分示意图

Figure 3. Grid distribution

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图 4 不同网格时截面平均时均总压损失系数

Figure 4. Time-averaged total pressure loss coefficient averaged on the outlet section with different grids

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图 5 原型静叶片数值与试验结果对比

Figure 5. Comparison of original stator between numerical results and experimental results

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图 6 不同射流轴向位置下截面平均时均总压损失系数分布

Figure 6. Distribution of the time-averaged total pressure loss coefficient averaged on the outlet section at different axial positions of SJA

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图 7 不同射流轴向位置下节距平均总压损失系数沿叶高方向分布

Figure 7. Pitch-averaged total pressure loss coefficient distributionalong span at different axial positions of SJA

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图 8 不同射流轴向位置下时均总压损失系数云图

Figure 8. Time-averaged total pressure loss coefficient distribution at different axial positions of SJA

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图 9 不同射流轴向位置下静压系数沿叶高分布

Figure 9. Static pressure coefficient distribution along span at different axial positions of SJA

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图 10 不同射流轴向位置下吸力面及端壁表面极限流线

Figure 10. Distribution of limiting streamlines on the suction surface and end-wall surface at different axial positions of SJA

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图 11 不同射流轴向方案下的时均轴向速度

Figure 11. Time-averaged axial velocity at different axial positions of SJA

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图 12 SJA控制下不同时刻出口流场特性及损失分布

Figure 12. Flow field characteristics and loss distribution at different time points under SJA control

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图 13 不同周向位置下截面平均时均总压损失系数随射流压比的变化

Figure 13. Change of the time-averaged total pressure loss coefficient averaged on the outlet section with the jet pressure ratio at different circumferential positions

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图 14 不同轴向位置下截面平均时均总压损失系数随射流压比的变化

Figure 14. Change of the time-averaged total pressure loss coefficient averaged on the outlet section with the jet pressure ratio at different axial positions

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图 15 SJA在不同射流偏角时的流线图

Figure 15. Streamlines at different jet deflection angles

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图 16 不同射流偏角下截面平均时均总压损失系数随射流压比的变化

Figure 16. Change of the time-averaged total pressure loss coefficient averaged on the outlet section with the jet pressure ratio at different jet deflection angles

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图 17 不同射流偏角下时均总压损失系数云图沿轴向的分布

Figure 17. Time-averaged total pressure loss coefficient distribution at different jet deflection angles along the axis

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表 1 叶栅几何气动参数

Table 1. Geometric and aerodynamic parameters of the compressor cascade

参数	数值
轴向弦长 b/mm	117.3
弦长 c/mm	120
叶片高度 H/mm	160
节距 t/mm	74
几何进气角 β₁/（°）	32.123
几何出气角 β₂/（°）	7.877
折转角 Δβ/（°）	40
安装角 γ/（°）	12
来流马赫数 Ma	0.21

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表 2 SJA主要几何参数

Table 2. Main geometric parameters of the SJA

参数	数值
宽度 W/mm	13.6
长度 L/mm	16
高度 H_SJA/mm	1
出口喉部宽度 w/mm	2

下载: 导出CSV

参考文献(25)

[1]	MENG Qinghe,CHEN Shaowen,LI Weihang,et al. Numerical investigation of a sweeping jet actuator for active flow control in a compressor cascade[R]. ASME Paper GT2018-76052,2018.
[2]	OTTO C,TEWES P,LITTLE J C,et al. Comparison of fluidic oscillators and steady jets for separation control on a wall-mounted hump[R]. AIAA 2018-1281,2018.
[3]	OTTO C,TEWES P,LITTLE J C,et al. Comparison between fluidic oscillators and steady jets for separation control[J]. AIAA Journal,2019,57(12): 5220-5229.
[4]	OSTERMANN F,WOSZIDLO R,NAYERI C N,et al. Properties of a sweeping jet emitted from a fluidic oscillator[J]. Journal of Fluid Mechanics,2018,857: 216-238.
[5]	KOKLU M,OWENS L R. Flow separation control over a ramp using sweeping jet actuators[R]. AIAA 2014-2367,2014.
[6]	KOKLU M,PACK MELTON L G. Sweeping jet actuator in a quiescent environment[R]. AIAA 2013-2477,2013.
[7]	NICKOL C L,HALLER W J. Assessment of the performance potential of advanced subsonic transport concepts for NASA’s environmentally responsible aviation project[R]. AIAA 2016-1030,2016.
[8]	WHALEN E A,LACY D S,LIN J C,et al. Performance enhancement of a full-scale vertical tail model equipped with active flow control[R]. AIAA 2015-0784,2015.
[9]	王忠. 单出口振荡射流在流动控制中的应用研究[D]. 南京: 南京航空航天大学,2016. WANG Zhong. Application researches of single-outlet oscillating jets in fluid flow control[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2016. (in Chinese WANG Zhong. Application researches of single-outlet oscillating jets in fluid flow control[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese)
[10]	赵曈. 振荡射流器性能优化及应用[D]. 南京: 南京航空航天大学,2021. ZHAO Tong. Performance optimization and application of sweeping jet actuators[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2021. (in Chinese ZHAO Tong. Performance optimization and application of sweeping jet actuators[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2021. (in Chinese)
[11]	TEWES P,TAUBERT L,WYGNANSKI I. On the use of sweeping jets to augment the lift of a lambda-wing[R]. AIAA 2010-4689,2010.
[12]	SEELE R,GRAFF E,GHARIB M,et al. Improving rudder effectiveness with sweeping jet actuators[R]. AIAA 2012-3244,2012.
[13]	SEELE R,GRAFF E,LIN J,et al. Performance enhancement of a vertical tail model with sweeping jet actuators[R]. AIAA 2013-0411,2013.
[14]	SEELE R,TEWES P,WOSZIDLO R,et al. Discrete sweeping jets as tools for improving the performance of the V-22[J]. Journal of Aircraft,2009,46(6): 2098-2106.
[15]	PACK MELTON L G. Active flow separation control on a NACA 0015 wing using fluidic actuators [R]. AIAA 2014-2364,2014.
[16]	CHOEPHEL T,CODER J,MAUGHMER M. Airfoil boundary-layer flow control using fluidic oscillators[R]. AIAA 2012-2655,2012.
[17]	马志明. 基于流体振荡器的S形进气道畸变流动控制机理与方法研究[D]. 南京: 南京航空航天大学,2021. MA Zhiming. Flow control mechanism and method of fluidic oscillator on the distorted flow in S-shaped inlet[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2021. (in Chinese MA Zhiming. Flow control mechanism and method of fluidic oscillator on the distorted flow in S-shaped inlet[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2021. (in Chinese)
[18]	孟腾,董金钟,吴西云. 流体振荡器在进气道流动控制中的应用研究[J]. 科学技术与工程,2016,16(32): 319-324,341. MENG Teng,DONG Jinzhong,WU Xiyun. Active flow control with fluidic in S-shaped inlet[J]. Science Technology and Engineering,2016,16(32): 319-324,341. (in Chinese MENG Teng, DONG Jinzhong, WU Xiyun. Active flow control with fluidic in S-shaped inlet[J]. Science Technology and Engineering, 2016, 16(32): 319-324, 341. (in Chinese)
[19]	王士奇. 流体振荡器: 一种有前途的非稳态激励器[J]. 航空动力,2022(1): 18-21. WANG Shiqi. Fluidic oscillator: a promising unsteady actuator[J]. Aerospace Power,2022(1): 18-21. (in Chinese WANG Shiqi. Fluidic oscillator: a promising unsteady actuator[J]. Aerospace Power, 2022(1): 18-21. (in Chinese)
[20]	孟庆鹤,李伟航,陈绍文,等. 扫频式射流对涡轮叶栅间隙泄漏流动影响的数值研究[J]. 推进技术,2020,41(6): 1250-1257. MENG Qinghe,LI Weihang,CHEN Shaowen,et al. Numerical study for effects of sweeping jets on tip clearance flow in a turbine cascade[J]. Journal of Propulsion Technology,2020,41(6): 1250-1257. (in Chinese MENG Qinghe, LI Weihang, CHEN Shaowen, et al. Numerical study for effects of sweeping jets on tip clearance flow in a turbine cascade[J]. Journal of Propulsion Technology, 2020, 41(6): 1250-1257. (in Chinese)
[21]	CHEN Shaowen,LI Weihang,YANG Pengcheng,et al. Aerodynamic performance and leakage flow in turbine cascades with sweeping jet actuators[J]. Journal of Turbomachinery,2023,145(6): 061015.
[22]	CHEN Shaowen,LI Weihang. Effects of combined sweeping jet actuator and winglet tip on aerodynamic performance in a turbine cascade[J]. Aerospace Science and Technology,2022,131: 107956.
[23]	孟庆鹤. 非定常射流控制轴流压气机叶栅角区分离的机理研究[D]. 哈尔滨: 哈尔滨工业大学,2021. MENG Qinghe. Research on the flow control mechanism of unsteady blowing on axial compressor cascade corner separation[D]. Harbin: Harbin Institute of Technology,2021. (in Chinese MENG Qinghe. Research on the flow control mechanism of unsteady blowing on axial compressor cascade corner separation[D]. Harbin: Harbin Institute of Technology, 2021. (in Chinese)
[24]	孟庆鹤,陈绍文,刘宏言,等. 扫频式射流对设计工况压气机叶栅流动分离影响的数值研究[J]. 推进技术,2020,41(3): 566-573. MENG Qinghe,CHEN Shaowen,LIU Hongyan,et al. Numerical study for effects of sweeping jets on separation in a compressor cascade at designed condition[J]. Journal of Propulsion Technology,2020,41(3): 566-573. (in Chinese MENG Qinghe, CHEN Shaowen, LIU Hongyan, et al. Numerical study for effects of sweeping jets on separation in a compressor cascade at designed condition[J]. Journal of Propulsion Technology, 2020, 41(3): 566-573. (in Chinese)
[25]	LU Weiyu,JIAO Yanmei,FU Xin. Concept of self-excited unsteady flow control on a compressor blade and its preliminary proof by numerical simulation[J]. Aerospace Science and Technology,2022,123: 107498.