Numerical Investigation of Three-dimensional Separation Control on a High-speed Compressor Stator Vane with Tailored Synthetic Jet
-
Yong Qin
,
Yanping Song
Abstract
A numerical study on the performance of synthetic jet for flow separation control on a high-speed compressor stator vane is performed. Four control schemes including full-span and part-span configurations are investigated at both design and off-design conditions. Results indicate that both full-span and part-span schemes could effectively delay flow separation and reduce total pressure loss for the compressor stator vane, the adaptability of the flow control under off-design conditions is also validated. Within the investigated incidence range, the full-span configuration is able to gain the most significant performance improvement, by which a maximum loss reduction of 23.8 % is obtained at i=2 deg. The part-span configuration could reorganize the vortex structures more efficiently and cut off the interaction between the ring-like vortex and the passage vortex, thus improving its performance in the corner region. In terms of flow control efficiency, the part-span configurations turn out to be more superior, where the highest control efficiency of 614.0 % is achieved at i=0 deg with the total height of the actuator being 40 %H. The flow control efficiency for all the schemes is higher than 100 % within the whole operating range, demonstrating a promising prospect for the application of synthetic jet in axial compressors.
Funding statement: This work is supported by the National Natural Science Foundation of China (Grant No. 51306042).
Nomenclature
- AF
Area of the jet exit of the actuator
- C
Blade chord length (mm)
- v1,v2
Velocity at the inlet and outlet evaluation planes
- Cx
Axial blade chord length (mm)
- Cp
Static pressure coefficient or static pressure rise coefficient
- CSV
Concentrated shed vortex
- CV
Corner vortex
- F+
Dimensionless actuation frequency
- f
Actuation frequency
- DH
De-Haller number
- H
Blade height (mm)
- h
Depth of the synthetic jet actuator (mm)
- i
Incidence angle (°)
- L.E.
Leading edge
- Ma
Mach number
- Ωij
Rate of strain tensor
- ORI
Baseline cascade
- p1, p2
Static pressure at the inlet and outlet evaluation planes
- pt,1, pt,2
Total pressure at the inlet and outlet evaluation planes
- PV
Passage vortex
- q
Dynamic pressure at the inlet plane
- Re
Reynolds number
- Sij
Rate of rotation tensor
- SJ
Synthetic jet
- SSA, SSB, SSC, SSD
Actuated cases
- SSV
Suction surface vortex
- t
Blade pitch (mm), time (s)
- T.E.
Trailing edge
- Umax
Maximum jet velocity
- WF
Injected energy by the synthetic jet
- WG
Aerodynamic performance gain
- w
Width of the actuator (mm)
- x, y, z
Coordinate (mm)
- β1
Inlet flow angle (°)
- β2
Inlet flow angle (°)
- γ
Stagger angle (°)
- θSJ
Jet angle (°)
- ρ
Density of jet flow (kg/m3)
- ωp
Profile loss coefficient
- ωs
Secondary flow loss coefficient
- ωt
Total pressure loss coefficient
- Δβ
Camber angle (°)
- Δωt
Relative total pressure loss coefficient
References
1. Prandtl L. The generation of vortices in fluids of small viscosity. Aeronaut J 1927;31(200):718–41.10.1017/S0368393100139872Search in Google Scholar
2. Gbadebo SA, Cumpsty NA, Hynes TP. Three-dimensional separations in axial compressors. J Turbomach 2005;127(2):331–39.10.1115/GT2004-53617Search in Google Scholar
3. Lei VM, Spakovszky ZS, Greitzer EM. A criterion for axial compressor hub-corner stall. J Turbomach 2008;130(3):031006.10.1115/GT2006-91332Search in Google Scholar
4. Dong Y, Gallimore SJ, Hodson HP. Three-dimensional flows and loss reduction in axial compressors. J Turbomach 1987;109(3):354–61.10.1115/86-GT-193Search in Google Scholar
5. Zhang Y, Mahallati A, Benner M. Experimental and numerical investigation of corner stall in a highly-loaded compressor cascade. ASME Paper No. GT2014-27204, 2014.10.1115/GT2014-27204Search in Google Scholar
6. Huanlong C, Turner MG, Siddappaji K, Mahmood SM. Vorticity dynamics based flow diagnosis for a 1.5-stage high pressure compressor with an optimized transonic rotor. ASME Paper No. GT2016-56682, 2016.Search in Google Scholar
7. Radespiel R, Burnazzi M, Casper M, Scholz P. Active flow control for high lift with steady blowing [J]. Aeronaut J 2016;120(1223):171–200.10.1017/aer.2015.7Search in Google Scholar
8. Culley DE, Bright MM, Prahst PS. Active flow separation control of a stator vane using embedded injection in a multistage compressor experiment. J Turbomach 2004;126(1):24234.10.1115/1.1643912Search in Google Scholar
9. Suder KL, Hathaway MD, Thorp SA, Strazisar AJ, Bright MB. Compressor stability enhancement using discrete tip injection. J Turbomach 2001;123(1):14–23.10.1115/2000-GT-0650Search in Google Scholar
10. Brück C, Tiedemann C, Peitsch D. Experimental investigations on highly loaded compressor airfoils with active flow control under non-steady flow conditions in a 3D-annular low-speed cascade. ASME Paper No. GT2016-56891, 2016.10.1115/GT2016-56891Search in Google Scholar
11. Liu HP, Li DY, Lu BX, Yu MH. Endwall secondary flow control in a high speed compressor cascade with vortex generator jets. ASME Paper No. GT2016-56843, 2016.10.1115/GT2016-56843Search in Google Scholar
12. Feng YY, Song YP, Chen F, Liu HP. Effect of endwall vortex generator jets on flow separation control in a linear compressor cascade. Proc Inst Mech Eng G J Aerosp Eng 2015;229(12):2221–30.10.1177/0954410015573340Search in Google Scholar
13. Li LT, Song YP, Chen F, Liu HP. Effects of vortex generator jet on flow separations in bowed compressor cascades. ASME Paper No. GT2015-42308, 2015.10.1115/GT2015-42308Search in Google Scholar
14. Hecklau M, Wiederhold O, Zander V, King R, Nitsche W, Huppertz A, et al. Active separation control with pulsed jets in a critically loaded compressor cascade. AIAA J 2011;49(8):1729–39.10.2514/6.2010-4252Search in Google Scholar
15. Smith BL, Glezer A. The formation and evolution of synthetic jets. Phys Fluids 1998;10(9):2281–97.10.1063/1.869828Search in Google Scholar
16. Savas Ö, Coles D. Coherence measurements in synthetic turbulent boundary layers. J Fluid Mech 1985;160:421–46.10.1017/S0022112085003548Search in Google Scholar
17. Zhang PF, Wang JJ, Feng LH. Review of zero-net-mass-flux jet and its application in separation flow control. Sci China Technol Sci 2008;51(9):1315–44.10.1007/s11431-008-0174-xSearch in Google Scholar
18. Glezer A, Amitay M. Synthetic jets. Annu Rev Fluid Mech 2002;34(1):503–29.10.1146/annurev.fluid.34.090501.094913Search in Google Scholar
19. Schaeffler NW. The interaction of a synthetic jet and a turbulent boundary layer. AIAA Paper No. 2003-643, 2003.10.2514/6.2003-643Search in Google Scholar
20. Amitay M, Kibens V, Parekh D, Glezer A. The dynamics of flow reattachment over a thick airfoil controlled by synthetic jet actuators. AIAA Paper No. 99-1001, 1999.10.2514/6.1999-1001Search in Google Scholar
21. Braunscheidel EP, Culley DE, Zaman KB. Application of synthetic jets to reduce stator flow separation in a low speed axial compressor. AIAA Paper No. 2008-602, 2008.10.2514/6.2008-602Search in Google Scholar
22. Matejka M, Popelka L, Safarik P, Nozicka J. Influence of active methods of flow control on compressor blade cascade flow. ASME Paper No. GT2008-51109, 2008.10.1115/GT2008-51109Search in Google Scholar
23. Zander V, Hecklau M, Nitsche W, Huppertz A, Swoboda M. Active flow control by means of synthetic jets on a highly loaded compressor cascade. Proc Inst Mech Eng A J Power Energy 2011;225(7):897–908.10.1177/0957650911410275Search in Google Scholar
24. Zander V, Nitsche W. Control of secondary flow structures on a highly loaded compressor cascade. Proc Inst Mech Eng A J Power Energy 2013;227(6):674–82.10.1177/0957650913495538Search in Google Scholar
25. De Giorgi MG, De Luca CG, Ficarella A, Marra F. Comparison between synthetic jets and continuous jets for active flow control: application on a NACA 0015 and a compressor stator cascade. Aerosp Sci Technol 2015;43:256–80.10.1016/j.ast.2015.03.004Search in Google Scholar
26. Benini E, Biollo R, Ponza R. Efficiency enhancement in transonic compressor rotor blades using synthetic jets: a numerical investigation. Appl Energ 2011;88(3):953–62.10.1016/j.apenergy.2010.08.006Search in Google Scholar
27. Hergt A, Meyer R, Liesner K, Nicke E. A new approach for compressor endwall contouring. ASME Paper No. GT2011-45858, 2011.10.1115/GT2011-45858Search in Google Scholar
28. Hunt JC, Wray AA, Moin P Eddies, streams, and convergence zones in turbulent flows [R]. Center for Turbulence Re-search, Tech. Report No. CTR-S88, 1988.Search in Google Scholar
29. Kang S, Hirsch C. Three dimensional flow in a linear compressor cascade at design conditions. ASME Paper No. 91-GT-114, 1991.10.1115/91-GT-114Search in Google Scholar
30. Siemann J, Krenz I, Seume JR. Experimental investigation of aspiration in a multi-stage high-speed axial-compressor. ASME Paper No. GT2016-56440, 2016.10.1115/GT2016-56440Search in Google Scholar
31. De Giorgi MG, Traficante S, De Luca CG, Bello D, Ficarella A. Active flow control techniques on a stator compressor cascade: a comparison between synthetic jet and plasma actuators. ASME Paper No. GT2012-69535, 2012.10.1115/GT2012-69535Search in Google Scholar
© 2017 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Estimation of Characteristic Data of Aircraft Engine Compressor based on Developed Modeling Method
- Conjugate Heat Transfer Analysis on the Interior Surface of Nozzle Guide Vane with Combined Impingement and Film Cooling
- Prediction of Lean Blowout Limits for Methane-Air Bluff Body Stabilized Combustion using a Temperature Gradient Method in a Model Gas-Turbine Afterburner
- Investigation of Film Cooling Effectiveness of Dual-fanned Hole with Various Exit Widths
- Performance Seeking Control of Propfan Engines Based on Modified Cuckoo Search
- A New Scheduling Method for TTCAN-Based Turbofan Distributed Control System
- Numerical Investigation of Three-dimensional Separation Control on a High-speed Compressor Stator Vane with Tailored Synthetic Jet
- Aerodynamic Optimization of Winglet-Cavity Tip in an Axial High Pressure Turbine Stage
- Estimation of Gas Turbine Unmeasured Variables for an Online Monitoring System
Articles in the same Issue
- Frontmatter
- Estimation of Characteristic Data of Aircraft Engine Compressor based on Developed Modeling Method
- Conjugate Heat Transfer Analysis on the Interior Surface of Nozzle Guide Vane with Combined Impingement and Film Cooling
- Prediction of Lean Blowout Limits for Methane-Air Bluff Body Stabilized Combustion using a Temperature Gradient Method in a Model Gas-Turbine Afterburner
- Investigation of Film Cooling Effectiveness of Dual-fanned Hole with Various Exit Widths
- Performance Seeking Control of Propfan Engines Based on Modified Cuckoo Search
- A New Scheduling Method for TTCAN-Based Turbofan Distributed Control System
- Numerical Investigation of Three-dimensional Separation Control on a High-speed Compressor Stator Vane with Tailored Synthetic Jet
- Aerodynamic Optimization of Winglet-Cavity Tip in an Axial High Pressure Turbine Stage
- Estimation of Gas Turbine Unmeasured Variables for an Online Monitoring System
