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Tytuł artykułu

Mixing and flame holding characteristics in two-dimensional supersonic stream with perpendicular injection

Wybrane pełne teksty z tego czasopisma
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
This paper reports the mixing of hydrogen in a supersonic airstream and the fIame holding capability of the combustion chamber. In particular, two-dimensional Navier-Stokes equations have been solved to see the effects of injector positions on mixing and fIame holding in a supersonic combustor. An explicit Harten-Yee Non-MUSCL Modified-fIux-type TVD scheme has been used to solve the system of equations, and a zeroequation algebraic turbulence model to ca1culate the eddy viscosity coefficient. The performance of combustor has been investigated by varying the distance of injector position from the left boundary keeping constant the backward-facing step height and other ca1culation parameters. The results show that the configuration for small distances of injector position has high mixing efficiency but the upstream recirculation cannot evolve properly which is an important factor for fIame holding capability. On the other hand, the configuration for very long distance has lower mixing efficiency due to lower gradient of hydrogen mass concentration on the top of the injector caused by the expansion of side jet both upstream and downstream of the injector. For moderate distances of injector position, large and elongated upstream recirculation can evolve which might be activated as a good flame holder.
Rocznik
Strony
5--20
Opis fizyczny
Bibliogr. 16 poz., wykr.
Twórcy
autor
autor
  • Department of Mechanical Engineering Bangladesh University of Engineering and Technology Dhaka - 1000, BANGLADESH, mali_buet@yahoo.com
Bibliografia
  • Ali M. and Fujiwara T. (2005): A numerical study on the mixing of air and hydrogen in a scramjet combustor. - The Aeronautical Journal, vol.109, No.1097, pp.325-335.
  • Ali M., Fujiwara T. and Leblanc J.E. (2001): The effects of Backward-Facing step on mixing and flame holding in supersonic combustor. - Journal of Energy, Heat and Mass Transfer, vol.23, pp.319-338.
  • Ali M. and Islam A.K.M.S. (1999): Effect of main flow inlet width on penetration and mixing of hydrogen in scramjet combustor. - Proceedings of the Eighth Asian Congress of Fluid Mechanics, December 6-10, Shenzhen, China, pp.647-650.
  • Baldwin B.S. and Lomax H. (1978): Thin layer approximation and algebraic model for separated turbulent flows. - AIAA Paper, pp.78-257.
  • Brown G.L. and Roshko A. (1974): On density effects and large structure in turbulent mixing layer. - J. Fluid Mechanics, vol.64, No.4, pp.775-816.
  • Heister S.D., Nguyen T.T. and Karagozian A.R. (1989): Modeling of liquid jets injected transversely into a supersonic crossflow. - AIAA Journal, vol.27, No.12, pp.1727-1734.
  • Kraemer G.O. and Tiwari S.N. (1983): Interaction of Two-Dimensional Transverse Jet with a Supersonic Mainstream. - NASA CR 175446.
  • Moss J.N. (1974): Reacting Viscous-Shock-Layer Solutions with Multicomponent Diffusion and Mass Injection. - NASA TR-411.
  • Papamoschou D. and Roshko A. (1986): Observation of supersonic free shear layers. - AIAA Paper, pp.86-0162.
  • Rausch V.L., McClinton C.R. and Hicks J.W. (1997): Scramjet breath new life into hypersonics. - Aerospace America, pp.40-46.
  • Reid R.C. and Sherwood T.K. (1966): The Properties of Gases and Liquids, Second Edition. - New York: McGraw-Hill.
  • Rogers R.C. (1971): A Study of the Mixing of Hydrogen Injected Normal to a Supersonic Airstream. - NASA TN D-6114.
  • Tabejamaat S.J.U.Y. and Niioka T. (1997): Numerical simulation of secondary combustion of hydrogen injected from Preburner into supersonic airflow. - AIAA Journal, vol.35, No.9.
  • Weidner E.H. and Drummond J.P. (1981): A Parametric Study of Staged Fuel Injector Configurations for Scramjet Applications. - AIAA Paper 81-11468.
  • White F.M. (1974): Viscous Fluid Flow. - New York: McGraw-Hill.
  • Yokota K. and Kaji S. (1996): The three-dimensional supersonic flow and mixing fields with a perpendicular air injection from a finite length slit. - Trans. Japan Soc. Aero. Space Sci., vol.39, No.124, pp.173-183.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-BPZ2-0035-0001
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