Numerical Investigation of a Complete Scramjet Demonstrator Model for Experimental Testing Under Flight Conditions

Simsont, Yann Hendrik; Gerlinger, Peter; Aigner, Manfred

doi:10.1007/978-3-642-33374-3_15

Cited by 2 publications

(3 citation statements)

References 12 publications

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“…Numerical studies have been performed to analyze variations of the strut geometry and fuel injection areas with regard to the mixing and combustion performances. In addition to these more fundamental studies which have been conducted for model combustors under laboratory conditions, the lobed strut injector has also been investigated in a complete scramjet demonstrator model at real flight conditions .…”

Section: Scramjet Strut Injector Simulationmentioning

confidence: 99%

“…In order to achieve a short length for a scramjet combustion chamber, rapid mixing of fuel and air is essential. Two main concepts for fuel placement can be distinguished: wall and strut injectors . Wall injectors supply the fuel through the combustor walls or through wall‐mounted ramps either in crossflow or at a chosen angle to the main flow.…”

Section: Introductionmentioning

confidence: 99%

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High order numerical simulation of the thermal load on a lobed strut injector for scramjet applications

Simsont

Gerlinger

2016

Numerical Methods in Fluids

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SUMMARYIn this paper, the thermal load on an actively cooled lobed strut injector for scramjet (supersonic combustion ramjet) applications is investigated numerically. This requires coupled simulations of the strut internal and external flow fields together with the heat conduction in the solid injector body. In order to achieve a fast mixing, the lobed strut is positioned at the channel axis to inject hydrogen into the core of a Mach 3 air stream. There it is exposed to the extremely high temperatures of the high speed flow. While the external air and hydrogen flows are supersonic, the strut internal hydrogen flow is mainly subsonic, in some regions at very low Mach numbers. To enable a simulation of the internal flow field which ranges from very low to very high Mach numbers (approximately Mach 2.25 at the nozzle exit), a preconditioning technique is employed. The compressible finite-volume scheme uses a spatially fourth order multi-dimensional limiting process discretization, which is used here for a first time to simulate a geometrically and fluid mechanically highly complex problem. It will be demonstrated that besides its high accuracy the multi-dimensional limiting process scheme is numerically stable even in case of demanding practical applications. The coupled simulation of the lobed strut injector delivers unique insight into the flow phenomena inside and outside the strut, the heat fluxes, the temperature distribution in the solid material, the required hydrogen mass flux with respect to cooling requirements and details concerning the conditions at the exit of the injector.

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Section: Scramjet Strut Injector Simulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

High order numerical simulation of the thermal load on a lobed strut injector for scramjet applications

Simsont

Gerlinger

2016

Numerical Methods in Fluids

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“…Within the collaborative research program GRK 1095 simulations of scramjet combustion chambers and complete scramjet models [13] are performed. Based on the simulations crucial processes in the combustor like mixing, ignition and flame stabilization are analyzed.…”

Section: Complete Scramjet Modelmentioning

confidence: 99%

Parallelization and Performance Analysis of an Implicit Compressible Combustion Code for Aerospace Applications

Keller¹,

Lempke²,

Simsont³

et al. 2014

High Performance Computing in Science and Engineering ‘14

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The compressible, implicit combustion code TASCOM3D is used with and without the spray module SPRAYSIM for different aerospace applications. A number of such cases and analysis of the performance of the code on massively parallel systems will be given. These include supersonic combustion simulations of a complete scramjet model, a model rocket combustor fueled with gaseous oxygen and hydrogen as well as two multiphase simulations. The evaporation of kerosene in a preheated, pressurized channel and the spray combustion in a LOX/GH 2 rocket combustor require an additional numerical tool to account for the liquid phase. Droplet propagation and evaporation is computed by the research code SPRAYSIM. Furthermore investigations with respect to the performance of the employed numerical codes are addressed. With respect to TASCOM3D the influence of block sizing on the performance is investigated intensively both in terms of weak and strong scaling. The strong scaling performance of SPRAYSIM is investigated for both multiphase simulations. It will be shown that both codes show a nearly ideal behavior.

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Numerical Investigation of a Complete Scramjet Demonstrator Model for Experimental Testing Under Flight Conditions

Cited by 2 publications

References 12 publications

High order numerical simulation of the thermal load on a lobed strut injector for scramjet applications

High order numerical simulation of the thermal load on a lobed strut injector for scramjet applications

Parallelization and Performance Analysis of an Implicit Compressible Combustion Code for Aerospace Applications

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