Experimental investigation of a SCRAMJET model combustor with injection through a swept ramp using laser-induced fluorescence with tunable excimer lasers

Honig, Richard E.; Theisen, Daniel; Fink, R.; Lachner, Rudolf; Kappler, G.; Rist, Dieter; Andresen, Peter L.

doi:10.1016/s0082-0784(96)80137-8

Cited by 13 publications

(4 citation statements)

References 9 publications

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“…The oblique shock augmented the recirculation zone length and increased the mixing of hydrogen fuel and air significantly. Flame anchoring and flame stabilization in a supersonic combustor have been accomplished using enhancement methods like struts (Rust, Gerlinger, and Aigner, 2010;Kumar, Das, and Sheelam, 2014;Ground et al, 2014;Bao et al, 2013), backward-facing step (Kumaran and Babu, 2009a), Diamond strut (Deepu, Gokhale, and Jayaraj, 2007), ramp (Hönig et al, 1996), pylon (Vergine et al, 2012), cavity (Ben-Yakar andHanson, 1998;Lee et al, 2013;Choi, Ma, and Yang, 2005;Baurle and Gruber, 1998;Grady et al, 2012), and combinations of these (Kumaran and Babu, 2009a;Grady et al, 2012). From the abovementioned practices, the strut-based parallel fuel injectors are preferred in most of the supersonic combustors, as the overall pressure loss associated with them is the least when compared to the normal injection.…”

Section: Introductionmentioning

confidence: 99%

Effect of added struts and intake velocity on flame stabilization in supersonic combustors

Mohammad

2021

JER is an international, peer-reviewed journal that publishes f

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In the present computational study, the impact of strut positions and the effect of inlet Mach numbers on the combustion efficiency are investigated in a strut-based supersonic combustor. An experimentally investigated model combustor developed at the German Aerospace Center (DLR) is simulated and validated. Then, a model combustor with three struts placed at different positions is investigated. Two-dimensional, compressible, reacting-flow governing equations are solved along with single-step chemistry reaction and k-ω SST turbulence model using a commercial CFD code FLUENT. The oblique shock from the struts has a profound influence on the mixing and combustion process. The H2O mole fraction, H2 mole fraction contours, and combustion efficiency of various configurations are compared for finding better mixing and flame stabilization. The combustion efficiency reduces when the two struts are located in farther downstream or placed at the same downstream location. At higher Mach numbers, the combustion is delayed, and the mixing of fuel with the supersonic mainstream is incomplete.

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Section: Introductionmentioning

confidence: 99%

Effect of added struts and intake velocity on flame stabilization in supersonic combustors

Mohammad

2021

JER is an international, peer-reviewed journal that publishes f

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“…Regarding the improvement of performances of these devices, there have been many reports of mixing enhancements under supersonic state 3,4) . Hönig R., et al 5) tested swept ramp and found that a combination of swept ramp and oblique shock improves mixing. Although there have been many efforts to clarify the mixing process and improve their performance, the flow energy loss cannot be avoided because the mixing process is considerably related to vortices that causes flow energy loss especially in a high speed flow situation.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Effect of Rods Inserted into Supersonic Main Flow on Porous Cavity Flow

Kuniyoshi

Yaga

Teruya

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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In this study, an experiment was performed to clarify the flow field, in which the rods were normally inserted into a main supersonic flow with a porous cavity. In the experiment, a porous cavity is attached to a bottom wall of a main duct. A thermal tuft probe was adopted to detect a vertical flow direction in the cavity to monitor the flow behavior in the cavity. The experiments show that the three rods aligned spanwise retard the downstream displacement of the starting shock wave. It also reveals that the interaction among the rods, the porous cavity, and the starting shock wave changes the flow in the cavity suggesting the strong circulation between the cavity and the main supersonic flow. Moreover, the frequency shift of the cavity flow from about 370Hz to 400Hz is confirmed during the displacement of the starting shock wave from upstream to downstream of the porous cavity.

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“…Supersonic mixing enhancements have attracted a great deal of attention because of the potential for important applications to scram jet engines [1] and thermal sprays [2], for example. A number of studies have investigated the mixing process under the supersonic state using various techniques, such as the use of a swept ramp [3], and a use of a contoured wall injector [4]. However, a number of problems, such as mixing losses, mixing efficiency [5], remain.…”

Section: Introductionmentioning

confidence: 99%

Study of Interaction between Supersonic Flow and Rods or Jets Surrounded by Porous Cavity

Kuniyoshi¹,

Yaga²,

Koda³

et al. 2012

OJFD

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In this experiment, the effects of the combination of jets or rods and a porous cavity on the supersonic flow field are studied by means of visualization of schlieren method and the measurements of wall static pressures and the flow direction in the cavity with the thermal tuft probe. Three cases of jets or rods arrangements are tested in the experiments. As a result, a bow shock wave which is generated by the jets or rods is observed by mean of schlieren method. And it is confirmed that the expansion region appears downstream of the rods but is not in case of the jets pattern. Moreover the pressure ratios of starting shock wave passing through porous cavity for jets pattern differ from that of rods pattern. In the cavity, the flow direction at the measurement position in the cavity is always opposite to the main flow, as long as the starting shock wave is located upstream of the porous cavity for all cases. Difference in the backward flow ratio between the jets and rods patterns is observe after the starting shock wave passes through the porous cavity.

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Experimental investigation of a SCRAMJET model combustor with injection through a swept ramp using laser-induced fluorescence with tunable excimer lasers

Cited by 13 publications

References 9 publications

Effect of added struts and intake velocity on flame stabilization in supersonic combustors

Effect of added struts and intake velocity on flame stabilization in supersonic combustors

Experimental Investigation of Effect of Rods Inserted into Supersonic Main Flow on Porous Cavity Flow

Study of Interaction between Supersonic Flow and Rods or Jets Surrounded by Porous Cavity

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