Numerical Exploration of Staged Transverse Injection into Confined Supersonic

Staged transverse sonic injection into supersonic flow in a confined environment usually employed in scramjet combustor has been explored numerically using an indigenously developed three-dimensional Reynolds Averaged Navier Stokes solver with Roe's scheme and k-w turbulence model. Simulations were carried out for both without injection and with injection in Mach 2 flow behind a backward-facing step in a rectangular duct. Simulation captured all finer details of flow structures including recirculation bubble behind a backward-facing step, barrel shocks and Mach discs caused due to transverse injection and reattachment of shear layer in the downstream wake region. K-w turbulence model with compressibility correction performed extremely well in predicting the overall behaviour of the flow field. The jet from the second injector was found to penetrate more in the free-stream due to the loss of free-stream total pressure across the barrel shock of the first injection point. Excellent agreement of computed profiles of various flow parameters at different axial locations in the duct with experimental results and other numerical results available in the literature demonstrate the robustness and accuracy of the indigenously developed code. Defence Science Journal, 2011, 61(1), pp.3-11 , DOI:http://dx.doi.org/10.14429/dsj.61.20

[1]  P. Manna,et al.  Numerical Investigation of Confinement Effect on Supersonic Turbulent Flow Past Backward Facing Step With And Without Transverse Injection , 2023, Journal of Aerospace Sciences and Technologies.

[2]  Steven Clark,et al.  Numerical investigation of a transverse jet for supersonic aerodynamic control , 1992 .

[3]  Dimitri Papamoschou,et al.  Observations of supersonic transverse jets , 1991 .

[4]  James C. McDaniel,et al.  Laser-induced-fluorescence visualization of transverse gaseous injection in a nonreacting supersonic combustor , 1988 .

[5]  M2.5 supersonic PIV measurements in a backward-facing step flow with normal injection , 2002 .

[6]  J. Philip Drummond,et al.  Numerical Study of Staged Fuel Injection for Supersonic Combustion , 1982 .

[7]  Tohru Mitani,et al.  Mixing Augmentation of Transverse Injection in Scramjet Combustor , 2000 .

[8]  P Manna,et al.  Numerical investigation of transverse sonic injection in a non-reacting supersonic combustor , 2005 .

[9]  James C. McDaniel,et al.  MOLE-FRACTION IMAGING OF TRANSVERSE INJECTION IN A DUCTED SUPERSONIC FLOW , 1991 .

[10]  Joseph A. Schetz,et al.  Structure of highly underexpanded transverse jets in a supersonic stream. , 1967 .

[11]  Timothy P. Parr,et al.  Combustion enhancement in supersonic coaxial flows , 1989 .

[12]  J. Mathew,et al.  Numerical Simulation of Transverse Injection of Circular Jets into Turbulent Supersonic Streams , 2008 .

[13]  Joseph Mathew,et al.  Improved Prediction of Plane Transverse Jets in Supersonic Crossflows , 2006 .

[14]  P. Roe.  CHARACTERISTIC-BASED SCHEMES FOR THE EULER EQUATIONS , 1986 .

[15]  Edward E. Zukoski,et al.  Secondary injection of gases into a supersonic flow , 1964 .

[16]  Yuji Ikeda,et al.  Mixing characteristics of normal injection into a supersonic backward-facing step flow measured with PIV , 2002 .

[17]  Goro Masuya,et al.  Penetration of jets injected behind backward-facing step in supersonic stream , 1999 .

[18]  D. Chakraborty,et al.  Numerical investigation of staged transverse sonic injection in Mach 2 stream in confined environment , 2003, The Aeronautical Journal (1968).

[19]  D. Wilcox.  Turbulence modeling for CFD , 1993 .

[20]  James C. McDaniel,et al.  Transverse injection into Mach 2 flow behind a rearward-facing step - A 3-D, compressible flow test case for hypersonic combustor CFD validation , 1991 .

[21]  R. C. Rogers,et al.  Numerical predictions of a rearward-facing-step flow in a supersonic combustor , 1989 .