An investigation of advanced fuel injection schemes for scramjet combustion

Baurle, Robert A.; Fuller, Raymond P.; White, J. A.; Chen, T.; Gruber, Mark; Nejad, A. S.

doi:10.2514/6.1998-937

Cited by 38 publications

(32 citation statements)

References 13 publications

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“…Like its predecessor the code solved the equations governing 2-and 3-D calorically perfect or thermally perfect nonequilibrium chemically reacting flows. The code used a structuredgrid, cell-centered, finite volume, density-based method [97,98].…”

Section: Hyper-x and A New Generation Of High-speed Reacting Flomentioning

confidence: 99%

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Methods for Prediction of High-Speed Reacting Flows in Aerospace Propulsion

Drummond

2014

AIAA Journal

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Section: Hyper-x and A New Generation Of High-speed Reacting Flomentioning

confidence: 99%

“…The code was used to evaluate the cold flow mixing effectiveness of two fuel injection schemes, a ramp injector, and a strut injector being considered for new scramjet designs [97]. The two injector designs are shown in Figs.…”

Section: Hyper-x and A New Generation Of High-speed Reacting Flomentioning

confidence: 99%

Methods for Prediction of High-Speed Reacting Flows in Aerospace Propulsion

Drummond

2014

AIAA Journal

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“…In order to further develop the scramjet engine, various researchers have implemented several fuel injection technics [4]. One of the popular injection schemes for scramjet engine is transverse injection of fuel into supersonic cross flow [5,6]. This results in formation of bow shock which is normal to the supersonic cross flow.…”

Section: Introductionmentioning

confidence: 99%

Assessment of RNG k-ε, SST K- ω and Reynolds Stress Models For Numerical Simulation of DLR Scramjet Engine

Debnath¹,

Tjprc²

2019

IJMPERD

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In recent years, many researchers have used numerical simulation to investigate scramjet engine because, setting up of testing facilities for scramjet engine is very expensive. Completion of simulation work in less time is costeffective but, it is also important to achieve good outcome from the simulation work. In this context, the use of appropriate turbulent model for the simulation for DLR scramjet engine is a vital aspect. From the available literature, it is seen that many researchers have used Reynolds stress, SST kω and RNG k-ε models in the field of supersonic flow and combustion. Thus, in this study, the primary objective was to find the better turbulence model in between Reynolds stress, SST kω and RNG k-ε models for numerical simulation of DLR scramjet engine. Finally, from the study, it is found that using SST kω model for numerical simulation of DLR scramjet engine results in more accuracy at a lesser computational time.Impact Factor (JCC): 7.6197 SCOPUS Indexed Journal NAAS Rating: 3.11The simulation in this study is conducted on a workstation equipped with Intel Xenon processor of 8 GB memory.The computational time spend for cold flow simulation using RNG k-ε and SST k-ω models were approximately 16 hours and that for using Reynolds Stress model was 31 hours. Whereas, the computational time spends for reactive flow simulation using RNG k-ε and SST k-ω models were approximately 36.5 hours and that for using Reynolds Stress model was approximately 74 hours. CONCLUSIONSIn this study, the primary objective was to find the better turbulence model in between Reynolds stress, SST kω and RNG k-ε models for numerical simulation of DLR scramjet engine. Base on the results found from the simulations, the following conclusions are drawn.• The results predicted by SSTk-ω model is found to be more accurate than the results predicted by RNG k-ε and Reynolds Stress models in comparison with experimental results.• In reference to the results obtained by using SSTk-ω model, it is seen that the average deviation in mixing and combustion efficiency predicted by RNG k-ε model is less compared with Reynolds Stress model.• The computational time required for simulations using RNG k-ε and SST k-ω models are substantially less in comparison with Reynolds Stress model.• Thus, from this study, it can be finally establish that the use of SST kω model for numerical simulation of DLR scramjet engine will provide more accurate result at a lesser computational time.

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“…The computer design tools are widely used in developing the optimum characteristics of the combustion chamber of different types [6], which must guarantee ignition and effective operation within the wide range of Mach numbers [7][8]. The main parameters to evaluate efficiency of the combustion chamber are the mixture degree, ignition condition, combustion efficiency and pressure losses.…”

Section: Introductionmentioning

confidence: 99%