Numerical investigation of the effect of self-excited sweeping jet actuator on flow separation in a compressor cascade
-
Yanchun Shi
,
Cong Zeng
Abstract
To address the issue of flow separation in an axial compressor cascade, this study explores the application of sweeping jet actuator (SJA) technology for active flow control. An unsteady numerical simulation method is employed to investigate the effect of self-excited jet injection from the blade surface on separation control. The influence of different SJA installation configurations and the resulting flow field characteristics are analyzed and discussed. Additionally, the adaptability of SJA control under various inlet conditions is examined. The results indicate that the self-excited sweeping jet can effectively reduce flow separation losses in the cascade, with a maximum reduction of up to 8.01 %. The SJA demonstrates favorable control performance across a range of inlet Mach numbers and exhibits good adaptability at positive incidence angles. However, at negative incidence, a slight increase in total pressure loss coefficient may occur.
Acknowledgments
The authors disclose receipt of the following financial support for the research of this article: This work was supported by the National Natural Science Foundation of China (No. U2233207) and Aeronautical Science Foundation of China (2023M039077001).
-
Research ethics: Not applicable.
-
Informed consent: Not applicable.
-
Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission. Yanchun Shi: Writing – original draft, Investigation, Analysis, Data curation. Cong Zeng: Writing – review & editing, Formal analysis, Methodology. Shaowen Chen: Writing – review & editing, Supervision, Funding acquisition.
-
Use of Large Language Models, AI and Machine Learning Tools: None declared.
-
Conflict of interest: The authors state no conflict of interest.
-
Research funding: National Nature Science Foundation of China (No. U2233207) and Aeronautical Science Foundation of China (2023M039077001).
-
Data availability: Not applicable.
-
Dual Submission/Publication: No, this manuscript and the results/data/figures contained in it have not been published elsewhere, nor are they under consideration (from you or one of your contributing authors) by another publisher.
Nomenclature
- BSN
-
Blade spiral node
- RANS
-
Reynolds-averaged Navier-Stokes
- SST
-
Shear stress transport
- PS/SS
-
Pressure/Suction side
- LE/TE
-
Leading/ Trailing edge
- SJA
-
Sweeping jet actuator
- Ma
-
Mach number
- h
-
Blade height (mm)
- l
-
Chord length (mm)
- m
-
Mass flowrate (kg/s)
- p
-
Static pressure (Pa)
- p *
-
Total pressure (Pa)
- y +
-
Dimensionless wall distance
- γ
-
Stagger angle (°)
- β
-
Flow angle (°)
- C pt
-
Total pressure loss
- ω
-
Total pressure loss coefficient
- C ps
-
Static pressure coefficient
Subscript
- 0
-
Inlet plane
- 1
-
Exit plane
- On
-
Cascade with SJA
- Off
-
Cascade without SJA
References
1. Meng, QH, Chen, SW, Li, WH. Numerical investigation of a sweeping jet actuator for activeflow control in a compressor cascade. In: ASME turbo expo turbine technical conference and exposition. New York, USA: American Society of Mechanical Engineers, GT2018-76052; 2018.10.1115/GT2018-76052Search in Google Scholar
2. Otto, C, Tewes, P, Little, JC. Comparison of fluidic oscillators and steady jets for separation control on a wall-mounted Hump//2018 AIAA aerospace sciences meeting. Atlanta, USA: American Institute of Aeronautics and Astronautics; 2018:1281.Search in Google Scholar
3. Otto, C, Tewes, P, Little, JC, Woszidlo, R. Comparison between fluidic oscillators and steady jets for separation control. AIAA J 2019:1–10. https://doi.org/10.2514/1.j058081.Search in Google Scholar
4. Ostermann, F, Woszidlo, R, Nayeri, CN, Paschereit, CO. Properties of a sweeping jet emitted from a fluidic oscillator. J Fluid Mech 2018;857:216–38. https://doi.org/10.1017/jfm.2018.739.Search in Google Scholar
5. Ostermann, F, Woszidlo, R, Nayeri, CN, Paschereit, CO. Interaction between a jet emitted by a fluidic oscillator and a crossflow at a skew angle. San Diego, California: American Institute of Aeronautics and Astronautics; 2019. AIAA Paper No. 2019-0887.10.2514/6.2019-0887Search in Google Scholar
6. Koklu, M, Owens, LR. Flow separation control over a ramp using sweeping jet actuators//7th. In: AIAA flow control conference. Atlanta, Georgia: American Institute of Aeronautics and Astronautics; 2014:2367 p.10.2514/6.2014-2367Search in Google Scholar
7. Koklu, M, Pack Melton, LG. Sweeping jet actuator in a quiescent environment//43rd AIAA fluid dynamics conference. San Diego, California: American Institute of Aeronautics and Astronautics; 2013:2477 p.10.2514/6.2013-2477Search in Google Scholar
8. Nickol, CL, Haller, WJ. Assessment of the performance potential of advanced subsonic transport concepts for NASAs environmentally responsible aviation Project//54th AIAA aerospace sciences meeting. San Diego, California: American Institute of Aeronautics and Astronautics; 2016:1030.10.2514/6.2016-1030Search in Google Scholar
9. Whalen, EA, Lacy, DS, Lin, JC. Performance enhancement of a full-scale vertical tail model equipped with active flow Control//53rd AIAA aerospace sciences meeting. Kissimmee, Florida: American Institute of Aeronautics and Astronautics; 2015:0784.10.2514/6.2015-0784Search in Google Scholar
10. Zhong, WANG. Application researches of single-outlet oscillating jets in fluid flow control. Nanjing: Nanjing University of Aeronautics and Astronautics; 2016.Search in Google Scholar
11. Tong, ZHAO. Performance optimization and application of sweeping jet actuators. Nanjing: Nanjing University of Aeronautics and Astronautics; 2021.Search in Google Scholar
12. Tewes, P, Taubert, L, Wygnanski, I. On the use of sweeping jets to augment the lift of a lambda-wing//28th AIAA applied aerodynamics conference. Chicago, Illinois: American Institute of Aeronautics and Astronautics; 2010. AIAA 2010-4689.10.2514/6.2010-4689Search in Google Scholar
13. Seele, R, Graff, E, Gharib, M. Improving rudder effectiveness with sweeping jet actuators//6th AIAA flow control conference. New Orleans, Louisiana: American Institute of Aeronautics and Astronautics; 2012. AIAA 2012-3244.10.2514/6.2012-3244Search in Google Scholar
14. Seele, R, Graff, E, Lin, J. Performance enhancement of a vertical tail model with sweeping jet actuators//51st AIAA aerospace sciences meeting including the new Horizons forum and aerospace exposition, Grapevine, Texas: American Institute of Aeronautics and Astronautics, 2013: AIAA 2013-0411.10.2514/6.2013-411Search in Google Scholar
15. Seele, R, Tewes, P, Woszidlo, R, McVeigh, MA, Lucas, NJ, Wygnanski, IJ. et al.. Discrete sweeping jets as tools for improving the performance of the V-22. J Aircraft 2009;46:2098–106. https://doi.org/10.2514/1.43663.Search in Google Scholar
16. Pack, M, LaTunia, G. Active flow separation control on a NACA 0015 wing using fluidic actuators//7th AIAA flow control conference. Atlanta, Georgia: American Institute of Aeronautics and Astronautics; 2014. AIAA 2014-2364.Search in Google Scholar
17. Choephel, T, Coder, J, Maughmer, M. Airfoil boundary-layer flow control using fluidic oscillators//30th AIAA applied aerodynamics conference. New Orleans, Louisiana: American Institute of Aeronautics and Astronautics; 2012. AIAA 2012-2655.10.2514/6.2012-2655Search in Google Scholar
18. Qinhe, MENG. Research on the flow control mechanism of unsteady blowing on axial compressor cascade corner separation. Harbin: Harbin Institute of Technology; 2021.Search in Google Scholar
19. Yang, P, Chen, S, Liu, G, Xu, C. Corner separation control using sweeping jet actuator in a compressor cascade. J Turbomach 2024;146:104503. https://doi.org/10.1115/1.4065412.Search in Google Scholar
20. Lu, W, Jiao, Y, Fu, X. Concept of self-excited unsteady flow control on a compressor blade and its preliminary proof by numerical simulation. Aero Sci Technol 2022;123:107498. https://doi.org/10.1016/j.ast.2022.107498.Search in Google Scholar
21. Wang, S, Fan, B, Wan, N. Spray distribution characteristics of self-excited sweeping nozzle in high-speed airflow. J Propuls Technol 2025;46:144–55.Search in Google Scholar
22. Chen, H. Investigation on aerodynamics performance application slot injection technology in compound lean compressor cascades. Harbin: Harbin Institute of Technology; 2009.Search in Google Scholar
© 2025 Walter de Gruyter GmbH, Berlin/Boston
