Numerical prediction on the interaction between the incident shock wave and the transverse slot injection in supersonic flows

Abstract The incident shock wave has a great impact on the transverse injection flow field in supersonic flows, and it can improve the mixing efficiency between the incoming flow and the fuel. In the current study, the interaction between the incident shock wave and the transverse slot injection has been investigated numerically, and the influences of the size and the location of the ramp on the wall pressure profiles in the transverse slot injection flow field have been performed. Additionally, the swept angle of the ramp is set to be 15.784°, 28.158° and 35.974°, respectively. The obtained results show that the size of the ramp has a great impact on the transverse injection flow field, and the shock wave formed upstream of the injection slot moves towards the entrance of the channel with the increase of the swept angle of the ramp and the jet-to-crossflow pressure ratio. The transverse injection flow field is disturbed when the incident shock wave formed at the leading edge of the ramp is strong enough, and the separation regions both upstream and downstream of the injection slot increase with the increase of the intensity of the incident shock wave. The incident shock wave has a large impact on the mixing improvement between the incoming supersonic flow and the fuel.

[1]  A. Gupta,et al.  Evaluation of Oblique and Traverse Fuel Injection in a Supersonic Combustor , 2007 .

[2]  A. Panaras,et al.  Review of the physics of swept-shock/boundary layer interactions , 1996 .

[3]  Lin Ma,et al.  Flow-Field Analysis of a Typical Hydrogen-Fueled Dual-Mode Scramjet Combustor , 2012 .

[4]  M. R. Gruber,et al.  Mixing and Penetration Studies of Sonic Jets in a Mach 2 Freestream , 1995 .

[5]  Wei Huang,et al.  Research status of key techniques for shock-induced combustion ramjet (shcramjet) engine , 2010 .

[6]  Shigeru Aso,et al.  A study on supersonic mixing by circular nozzle with various injection angles for air breathing engine , 2006 .

[7]  E. Erdem,et al.  Numerical and experimental investigation of transverse injection flows , 2010 .

[8]  Wei Shyy,et al.  Supersonic jet and crossflow interaction: Computational modeling , 2013 .

[9]  H. Babinsky,et al.  Corner effect and separation in transonic channel flows , 2011, Journal of Fluid Mechanics.

[10]  Li Yan,et al.  Numerical validation and parametric investigation on the cold flow field of a typical cavity-based scramjet combustor , 2012 .

[11]  Zhenxun Gao,et al.  Numerical research on mixing characteristics of different injection schemes for supersonic transverse jet , 2011 .

[12]  William W. Liou,et al.  Turbulence model assessment for shock wave/turbulent boundary-layer interaction in transonic and supersonic flows , 2000 .

[13]  E. E. Zukoski,et al.  A Study of the Interaction of Gaseous Jets from Transverse Slots with Supersonic External Flows , 1968 .

[14]  Taku Kudo,et al.  Effect of the incident shock wave interacting with transversal jet flow on the mixing and combustion , 2011 .

[15]  Hwanil Huh,et al.  Numerical Study of Mixing Enhancement by Shock Waves in Model Scramjet Engine , 2003 .

[16]  Luca Maddalena,et al.  Molecular Weight and Shock-Wave Effects on Transverse Injection in Supersonic Flow , 2010 .

[17]  J.M.A. Longo,et al.  Assessment of CFD capability for prediction of hypersonic shock interactions , 2012 .

[18]  Ben Thornber,et al.  On the importance of generating accurate turbulent boundary condition for unsteady simulations , 2011 .

[19]  Lin Ma,et al.  Parametric effects in a scramjet engine on the interaction between the air stream and the injection , 2012 .

[20]  Jun Liu,et al.  Influences of the turbulence model and the slot width on the transverse slot injection flow field in supersonic flows , 2012 .

[21]  S. Baek,et al.  Numerical study on supersonic combustion with cavity-based fuel injection , 2004 .

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