Combustion characteristics of an inlet/supersonic combustor model

Gamba, Mirko; Miller, Victor A.; Mungal, M. G.; Hanson, Ronald K.

doi:10.2514/6.2012-612

Cited by 11 publications

(18 citation statements)

References 12 publications

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“…This changes towards the end of the combustor, where the flame boundary is smoother and the turbulent structures are not discernible, most likely a result of faster chemistry at this point in the combustion process, when completion rate is higher. This behaviour is quite different from the one observed by Gamba et al [40], as the flow in the engine is highly non-uniform and provides better mixing, leading to different flame structures. This will be analysed in more detail in the next section.…”

Section: Flame Visualisationcontrasting

confidence: 87%

“…The authors' conclusion was that more experimental data is required for proper understanding of the regime where supersonic combustion occurs. Finally, Gamba et al [39,40] performed experiments on a combustor with a shock generator to reproduce realistic scramjet combustor conditions. This is a relevant and important experiment in supersonic combustion and is discussed in detail here.…”

Section: Supersonic Turbulent Combustion Experimentsmentioning

confidence: 99%

“…Schematic of the combustor model used by Gamba et al[40]. the flow, but these are quickly dissipated amidst the shocks created by fuel injection.…”

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confidence: 99%

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Investigation of supersonic turbulent combustion in a Mach 10 scramjet engine

Moura¹

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A doctorate is by definition an individual project, but it would be hard to argue it is done on one's own. It's been four years of ups and downs and there are many people who supported me directly or indirectly: partner, friends, co-workers. Having moved into a new country with no one but my partner, these people have played an important role. Too important for the brief words I dedicate to them here. Most important of all I'd like to thank my partner, Luciana, for her support throughout this period. This experience would not have been as good if not for her being around to support me, especially when things seemed like they would fall apart. And when I had no confidence in myself, she did. Thank you for everything. Thank you to my parents, Dolores and Paulo, and my sister, Mariana, who supported me from across the world and were patient and understanding of mine coming here. Particularly my father, who I know was hit hardest by the distance. Thank you for supporting me through this career choice. Thank you to my supervisors, Ingo Jahn, Vince Wheatley and Tim McIntyre for the support and guidance over these years, and for the opportunity. Thank you to the new friends I made here in Australia for the fun times you made sure I had. Some moved on already to pastures new, some are still around. You know who you are. I hope we can keep in touch as our lives take us to different places. I'd like to thank Andreas, Juan and Pierpaolo, closest and constant over these years, those "hyperfools". They'll get it. Thank you to the T4 crew: Eric, Jens, Keith, Ryan, the other Ryan, Sam, Tristan, Will, Zac. Some of you operated the tunnel for me, all of you taught me something and helped me when I needed. You made my experiments possible, in both small and big ways. Thank you for the support. Many thanks to Wilson Chan and Michael Smart. Your help was the most invaluable when I was in the tunnel and helped me successfully concluded my experiments. Not enough can be said about your support. Lastly, but certainly not least, thank you to Nicholas Gibbons for his support with the simulations, particularly the LES. You've always been extremely supportive and never denied help, even towards the end when I was annoying you daily with small problems. Thank you very much for all the help. ix Financial support This thesis was completed with financial support from the Brazilian National Council of Scientific and Technological Development-CNPq.

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Section: Flame Visualisationcontrasting

confidence: 87%

Section: Supersonic Turbulent Combustion Experimentsmentioning

confidence: 99%

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Investigation of supersonic turbulent combustion in a Mach 10 scramjet engine

Moura¹

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“…Figure 4 displays the schematic of Gamba model combustor. 18 Hydrogen is injected through a 2 mm diameter injector located on the centerline of the plate, which has a spanwise width of 60 mm. Table 2 shows the inflow conditions for air and hydrogen.…”

Section: A Two-dimensional Simulation Of the Dlr Supersonic Combustormentioning

confidence: 99%

IDDES simulation of supersonic combustion using flamelet modeling

Wang

Piao

Niu

2015

22nd AIAA Computational Fluid Dynamics Conference

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A turbulent combustion modeling method combining the improved delayed detached eddy simulation (IDDES) model and the flamelet/progress variable (FPV) model is developed and then applied in the simulation of two supersonic combustors, namely the DLR supersonic combustor and the Gamba model combustor. Results show good agreement with the experiment, validating the accuracy of this method in supersonic combustion simulations. As a comparison, k-ω SST model combined with the FPV model is applied in the same cases. It is found that the simulation of k-ω SST model leads to larger deviations compared with that of the IDDES model, and the time cost of the IDDES model is only 3% more than that of the k-ω SST model. Moreover, the initial and boundary conditions of flamelet libraries are set to fixed values, thus can not account for the pressure and temperature variations in compressible flows. In response to this, a pressure and temperature correction of the FPV model is proposed and then applied in the DLR case. Results indicate that the correction method noticeably improves the accuracy of supersonic combustion simulations. Nomenclature Cp = specific heat coefficient at pressure constant C = progress variable h = specific enthalpy k = turbulent kinetic energy P = pressure Pr = Prandtl number Sc = Schmidt number T = temperature t = time Y = mass fraction Z = mixture fraction  = dissipation rate of turbulent kinetic energy  = dynamic viscosity  = density  = Scalar dissipation rate  = turbulent eddy frequency  = mass production rate Subscripts 0 = stagnation property i = species st = stoichiometric t = turbulent Superscripts

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“…In addition, many other experiments and numerical investigations were performed to examine the effect of varying inlet Mach number and fuel-air equivalence ratio on the nature and extent of the interaction between the combustor and inlet. (16)(17)(18) Some mechanisms that might contribute to this phenomenon were presented. These included separation of the boundary layer in the duct, formation of a detonation, and formation of shock waves by the region of thermally choked flow, and et al In some cases, the combustion-induced pressure rise was replaced with mechanical throttling of the flow.…”

Section: Introductionmentioning

confidence: 99%

Combustor-inlet interactions in a low-order dynamic model of ramjet engines

Liu

Cui

2020

Aeronaut. j.

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The coexistence of multiple stable states is indicative of self-organising processes occurring in the course of the combustor-inlet interactions in a ramjet engine and give rise to the appearance of various nonlinear phenomena. This paper provides a dynamic model that can describe the multiple stable states and the corresponding nonlinear effects to further investigate the dynamic interactions between combustor and inlet in a ramjet engine. Our study shows the whole engine can display distinct dynamic behaviours ranging from irreversibility to hysteresis and to various mode transitions, depending on different physical parameters. With the model, we also illustrate the role of the instability of the normal shock wave in impacting the whole engine’s nonlinear dynamics. Additionally, we extend the previous studies of the classification of combustor-inlet interactions from a static framework to a dynamic framework, which helps to clarify the transient processes of the nonlinear interactions. This work offers a quantitative illustration of the combustor-inlet interactions in a ramjet engine by revealing its nonlinear dynamics and associated characteristics, therefore advancing our understanding of the nonlinear phenomena that exhibit in ramjet engines.

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Combustion characteristics of an inlet/supersonic combustor model

Cited by 11 publications

References 12 publications

Investigation of supersonic turbulent combustion in a Mach 10 scramjet engine

Investigation of supersonic turbulent combustion in a Mach 10 scramjet engine

IDDES simulation of supersonic combustion using flamelet modeling

Combustor-inlet interactions in a low-order dynamic model of ramjet engines

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