Journal of computational fluids engineering (한국전산유체공학회지)

Korean Society of Computational Fluids Engineering (한국전산유체공학회)
권호 표지
DOI QR코드

DOI QR Code

SUPERSONIC INLET BUZZ CONTROL USING CORRECTED BLEED MODEL

보정한 Bleed 모델을 이용한 초음속 흡입구 버즈 제어

  • Kwak, E. (Dept. of Aerospace Engineering, Inha Univ.) ;
  • Lee, S. (Dept. of Aerospace Engineering, Inha Univ.)
  • 곽인근 (인하대학교 대학원 항공우주공학과) ;
  • 이승수 (인하대학교 항공.조선.산업.공학부 항공우주공학전공)
  • Received : 2013.11.02
  • Accepted : 2013.12.10
  • Published : 2013.12.31
Download PDF
⟨ Previous Next ⟩

Abstract

Database of a bleed model has been corrected and numerical simulations have been performed to control buzz using the corrected bleed model. The existing bleed model, which was developed as a part of a boundary condition model for porous bleed walls, underestimates bleed flow rate because flow accelerations near the bleed regions are ignored. Also, it overpredicts the sonic flow coefficient when the bleed plenum pressure ratio is high. To correct these problems, and to enhance the performance of the bleed model, the database has been corrected using CFD simulations to compensate for the flow acceleration near the bleed region. Futhermore, the database of the bleed model is extended with the second order extrapolation. The corrected bleed model is validated with numerical simulations of a shock-boundary layer interaction problem over a solid wall with a bleed region. Using the corrected bleed model, numerical simulations of supersonic inlet buzz are performed to find the deterrent effects of bleed on buzz. The results reveal that bleed is effective to prevent buzz and to enhance the inlet performance.

Keywords

References

  1. 1973, Syberg, J. and Hickox, T.E., "Design of a Bleed System for a Mach 3.5 Inlet," NASA CR-2187.
  2. 1968, Sanders, B.W. and Cubbison, R.W., "Effect of Bleed-System Back Pressure and Porous Area on the Performance of an Axisymmetric Mixed Compression Inlet at Mach 2.50," NASA TM X-1710.
  3. 1976, Shaw, R.J., Wasserbauer, J.F. and Neumann, H.E., "Boundary Layer Bleed System Study for a Full Scale, Mixed Compression Inlet with 45-Percent Contraction," NASA TM X-3358.
  4. 1988, Abrahamson, K.W. and Bower, D.L., "An Empirical Boundary Condition for Numerical Simulation of Porous Plate Bleed Flows," AIAA Paper 1988-0306.
  5. 1993, Paynter, G.C., Treiber, D.A. and Kneeling, W.D., "Modeling Supersonic Inlet Boundary Layer Bleed Roughness," AIAA Journal of Propulsion and Power, Vol.9-4, pp.622-627. https://doi.org/10.2514/3.23666
  6. 1994, Mayer, D.W. and Paynter, G.C., "Boundary Conditions for Unsteady Supersonic Inlet Analyses," AIAA Journal, Vol.32-6, pp.1200-1206. https://doi.org/10.2514/3.12120
  7. 1996, Harloff, G.J. and Smith, G.E., "Supersonic-Inlet Boundary-Layer Bleed Flow," AIAA Journal, Vol.34-4, pp.778-785. https://doi.org/10.2514/3.13140
  8. 2006, Akatsuka, J., Watanabe, Y., Murakami, A. and Honami, S., "Porous Bleed Model for Boundary Condition of CFD Analysis," AIAA Paper 2006-3682.
  9. 2008, Slater, J.W. and Saunders, J.D., "Modeling of Fixed-Exit Porous Bleed Systems," AIAA Paper 2008-0094.
  10. 2009, Slater, J.W., "Improvements in Modeling 90-degree Bleed Holes for Supersonic Inlets," AIAA Paper 2009-710.
  11. 1981, Roe, R.L., "Approximate Riemann Solvers, Parameter Vectors and Difference Schemes," Journal of Computational Physics, Vol.43-3, pp.357-372. https://doi.org/10.1016/0021-9991(81)90128-5
  12. 1976, Van Leer, B., "Towards the Ultimate Conservative difference Scheme. V. A. Second Order Sequel to Godunov's Method," Journal of Computational Physics, Vol.32-1, pp.101-136.
  13. 1982, Beam, R.M. and Warming, R.F., "Implicit Numerical Methods for the Compressible Navier-Stokes and Euler Equations," von Karman Institute for Fluid Dynamics Lecture Series.
  14. 1994, Menter, F.R., "Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications," AIAA Journal, Vol.32-8, pp.1598-1605. https://doi.org/10.2514/3.12149
  15. 1996, Willis, B.P. and Davis, D.O., "Boundary layer development downstream of a bleed mass flow removal region," AIAA Paper 96-3278.
  16. 1995, Willis, B.P., Davis, D.O. and Hingst, W.R., "Flowfield Measurements in a Normal-Hole-Bled Oblique Shock-Wave and Turbulent Boundary-layer Interaction," AIAA Paper 95-2885.
  17. 1972, Nagashima, T., Tornio, O. and Tsuyoshi, A., "Experiment of Supersonic Air Intake Buzz," Institute Space and Aeronautical Science, University of Tokyo, Japan, Rept. 481.
  18. 2013, Kwak, E., Lee, N., Gong. H. and Lee, S., "Numerical Simulations of Low- and High-Frequency Buzz around an Axisymmetric Supersonic Inlet," Journal of Computational Fluids Eng., Vol.18-2, pp.78-84. https://doi.org/10.6112/kscfe.2013.18.2.078
  19. 1954, Dailey, C.L., "Supersonic Diffuser Instability," Ph.D Thesis, California Institute of Technology.