Experimental study on mixing enhancement in two dimensional supersonic flow

Charyulu, B.V.N.; Kurian, Job; Venugopalan, Paloth; Sriramulu, V.

doi:10.1007/s003480050181

Cited by 10 publications

(4 citation statements)

References 21 publications

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“…In the design of a stainless cylindrical microcombustor, a critical component for micropower systems using hydrogen and hydrocarbon fuels as an energy source, Yang et al [28] used the backward facing step to provide a simple yet effective solution to enhance the mixing of the fuel mixture, prolong the residence time, control the position of the flame, and widen the operational range of the flow rate and H 2 /air ratio. Charyulu et al [7] studied mixing enhancement with two-dimensional (2D) lobed nozzles in a dual stream supersonic flow facility, and their results indicated an enormous enhancement in mixing when a 2D lobed nozzle was employed in comparison with a conventional plain 2D nozzle. The enhanced mixing performance could be attributed to the large-scale axial vortices observed in the flow field.…”

Section: Introductionmentioning

confidence: 99%

Mixing Enhancement by Optimal Flow Advection

Liu¹

2008

SIAM J. Control Optim.

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We consider the problem of optimal mixing control. Our objective is to best enhance mixing by flow advection while the flow is optimized in the sense that it is almost steady and is of the least magnitude and the least rotation. For this we define a mixing efficiency functional by penalizing the average of variance of a diffusive scalar, the average of the flow, and the average of its acceleration and strain tensor. By variational principles, we prove the existence of an optimal flow and derive optimality conditions that consist of a system of nonlinear advection-diffusion equations, wave equations, and Laplace's equation.

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Section: Introductionmentioning

confidence: 99%

Mixing Enhancement by Optimal Flow Advection

Liu¹

2008

SIAM J. Control Optim.

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“…Wall injectors, where hydrogen is injected through the wall [18][19][20] (normal or oblique to the main flow) or by ramps [21][22][23] mounted to the wall, Strut injectors [16,[24][25][26], which are located at the channel axis and directly inject the fuel into the core of the air stream.…”

Section: B Scramjet Fuel Injection Systemmentioning

confidence: 99%

CFD Analysis of Mixing and Combustion of a Scramjet Combustor with a Planer Strut Injector

Pandey¹,

Sivasakthivel²

2011

IJESD

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As one of the most promising propulsive systems in the future, the scramjet engine has drawn the attention of many researchers. The two-dimensional coupled implicit NS equations, the standard k-ε turbulence model and the finite-rate/eddy-dissipation reaction model have been applied to numerically simulate the flow field of the hydrogen fueled scramjet combustor with a planer strut flame holder under two different working conditions, namely, cold flow and engine ignition. The obtained results show that the numerical method used in this paper is suitable to simulate the flow field of the scramjet combustor. The static pressure distribution along the top and bottom walls for the case under the condition of engine ignition is much higher than that for the case under the condition of cold flow. There are three clear pressure rises on the top and bottom walls of the scramjet combustor. The eddy generated in the strut acts as a flame holder in the combustor, and it can prolong the residence time of the mixture in the supersonic flow.

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“…The earlier injection strategy involved transverse injection onto the oncoming supersonic crossflow [2][3][4][5][6][7][8]. Transverse injections lead to the formation of normal bow shock separating two regions of flow i.e.…”

Section: Introductionmentioning

confidence: 99%

Investigation of strut-ramp injector in a Scramjet combustor: Effect of strut geometry, fuel and jet diameter on mixing characteristics

Soni

2017

J Mech Sci Technol

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The strut based injector has been found to be one of the most promising injector designs for supersonic combustor, offering enhanced mixing of fuel and air. The mixing and flow field characteristics of the straight (SS) & tapered strut (TS), with fixed ramp angle and height at freestream Mach number 2 in conjunction with fuel injection at Mach 2.3 have been investigated numerically and reported. In the present investigation, hydrogen (H2) and ethylene (C2H4) are injected in oncoming supersonic flow from the back of the strut, where jet to freestream momentum ratio is maintained at 0.79 and 0.69 for H2 & C2H4, respectively. The predicted wall static pressure and species mole fractions at various downstream locations are compared with the experimental data for TS case with 0.6 mm jet diameter and found to be in good agreement. Further, the effect of jet diameter and strut geometry on the near field mixing in strut ramp configuration is discussed for both the fuel. The numerical results are assessed based on various parameters for the performance evaluation of different strut ramp configurations. The SS configuration for both the injectant is found to be an optimum candidate, also it is observed that for higher jet diameter larger combustor length is required to achieve satisfactory near field mixing.

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Experimental study on mixing enhancement in two dimensional supersonic flow

Cited by 10 publications

References 21 publications

Mixing Enhancement by Optimal Flow Advection

Mixing Enhancement by Optimal Flow Advection

CFD Analysis of Mixing and Combustion of a Scramjet Combustor with a Planer Strut Injector

Investigation of strut-ramp injector in a Scramjet combustor: Effect of strut geometry, fuel and jet diameter on mixing characteristics

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