Improving the efficiency of a serpentine inlet duct by using of Blowing Jet Vortex Generators flow control technique

Document Type : Mechanics article

Authors

Abstract

In this research, aerodynamic performance of a double s-shaped serpentine inlet duct is numerically investigated by using of blowing Jet vortex generators flow control technique. At first, turbulence equations are validated by comparing the numerical results with experimental test data of a standard inlet, and aerodynamic loss parameters of a sample serpentine inlet are estimated in flight condition of Mach=0.7 at Altitude=9000m. Then the effect of active flow control technic on the loss parameters are studied by installing two sets of 20 blowing vortex generators on the upper and lower walls of the duct in 5 separated and integrated arrangement schemes by simulating 0.01 and 0.02 blowing mass flow ratios. By comparing between 5 schemes with clean duct in the fields of blowing mass flow ratio, 2% blowing ratio has better improvement results in all schemes. In the field of arrangement position, C3 and C5 schemes respectively by 3.1% and 3.12% increase in total pressure recovery, 67.16% and 64.66% decrease in DC(60) distortion coefficient and 71.8% and 64.5% decrease in DPCP coefficient at 2% blowing mass flow ratio, are selected as the best flow control scheme.

Keywords

Main Subjects

References

 
 
[1]J.W. Hamstra, DN. Miller, PP. Truax, Active inlet flow control technology demonstration. Proceedings of the 22nd internal council of aeronautical sciences; 2000.
[2]M. B. Senseney, T. A. Buter, R. D. W. Bowersox, Performance Characterization of a Highly Offset Diffuser with Vortex Generator Jets, Journal of Propulsion and Power, Vol. 12, pp. 7,Mar-Apr, 1996.
[3]           B. D. McElwain, Unsteady sparation point injection for pressure recoveryi mprovement in high subsinic diffusers. M.Sc Thesis, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, MIT, 2002.
[4]           A. S. Luers, Flow control thechnics in serpentine inlet, M.Sc Thesis, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, MIT, 2003.
[5]           A. C. Rabe, Effectiveness of a Serpentine Inlet Duct Flow Control Scheme at Design, PhD Thesis, Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Virginia Polytechnic Institute and State University, 2003.
[6]           A. M. Pradeep, R. K. Sullerey, Secondary flow control in a circular S-duct diffuser using vortex generator jets.AIAA 2004-2615, in 2nd AIAA Flow ControlConference, Portland, Oregon, 2004.
[7]           N. A. Harrison, J. Anderson, J. L. Fleming, W. F. Ng, Computational analysis of active flow control of BLI inlet.AIAA 2006-874, in 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 2006.
[8]           R. K. Sullerey, V. S. Mangat, A. Padhi, Flow control in serpentine inlet using vortex generator jets.AIAA-2006-3499, in 3rd AIAA Flow Control Conference, San Francisco, California, 2006.
[9]           M. Debiasi, M. R. Herberg, Z. Yan, S. S. Dhanabalan, H. M. Tsai, Control of flow separation in S-ducts via flow injection-AIAA-2008-74, in 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 2008.
[10]         A. Gissen, B. Vukasinovic, M. McMillan, A. Glezer, Distortion management in a BLI inlet diffuser using synthetic jet hybrid flow control.AIAA2011-35-in 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, Florida, 2011.
[11]         N. V. Kale, Active and hybrid flow control in S-ducts and diffuser, Ph.D Thesis, Department of Aerospace Engineering, University of Illinois at Urbana-Champaign, Urbana, Illinois, 2013.
[12]         A. M. Kirk, A. Kumar, J. I. Gargoloff, O. K. Rediniotis, P. G. A. Cizmas, Numerical and experimental investigation of a serpentine inlet duct, in 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 2007.
[13]         Ansys, Ansys Fluent 15 Help, 2014.
[14]         J.Shedon, Intake Aerodynamic, Second ed., UK: Blackwell Science Ltd, 1999.
[15]         SAE, Inlet total pressure distortion considerations for gas turbine engines.SAE-AIR-1419A, Society of Automotive Engineers USA,  pp. 2011.
[16]         SAE, Gas turbine engine inlet flow distortionguidelines.SAE-ARP1420, Society of Automotive Engineers USA,  pp. 2002.
[17]         D. D. Sanders, M. G. List, CFD performance predictions of a serpentine diffuser configuration in an annular cascade facility.AIAA 2013-0220, in 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Grapevine (Dallas/Ft. Worth Region).Texas, 2013.
[18]         S. Kumar, B. Sasanapuri, K. A. Kurbatskii, A. Lestari, Pressure-based coupled simulation of pressure recovery and distortion in an S-shaped intake diffuser.AIAA 2013-3794, in 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, San Jose, CA, 2013.
[19]         T. M. Berens, A. L. Delot, M. Chevalier, J. v. Muijden, Numerical simulations for high offset intake diffuser flows.NLR-TP-2014-096, NLR, National Aerospace Laboratory NLR,  pp. 2014.
[20]         C. A. Nessler, W. W. Copenhaver, M. G. List, Serpentine diffuser performance with emphasis on future introduction to a transonic fan.AFRL-RQ-WP-TP-2014-0168, Vol. 1, Wright-Patterson Air Force Base, Air Force Research Laboratory, Aerospace Systems Directorate,  pp. 2014.
[21]         M. Rutten, S. Kuckenburgy, S. Koch, M. Rein, Investigation of the flow within partially submerged scoop type air intakes.AIAA 2013-2912, in 31st AIAA Applied Aerodynamics Conference, San Diego, CA, 2013.
[22]         L. R. Owens, B. G. Allan, S. A. Gorton, Boundary-layer-ingesting inlet flow control, Journal of Aircraft, Vol. 45, No. 4, July-August, 2008.
Journal of Modeling in Engineering
Volume 16, Issue 53
July 2018
Pages 9-23

Files

History

  • Receive Date: 28 December 2015
  • Revise Date: 01 January 2017
  • Accept Date: 02 May 2017

Share

How to cite

Statistics