Shock/Boundary Layer/Heat Release Interaction in the HyShot II Scramjet Combustor

Cecere, D.; Ingenito, Antonella; Romagnosi, Luigi; Bruno, Claudio; Giacomazzi, E.

doi:10.2514/6.2010-7066

Cited by 9 publications

(13 citation statements)

References 17 publications

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“…In the flight tests and experiments (emulated by the simulation) the approach flow encounters a 17° inclined ramp, compressing the approach flow, and after bleeding off the ramp boundary layer, the resulting flow enters the isolator. Cesare et al, [71], use combustor inflow conditions from Won et al, [142], including also the ramp intake in their two-dimensional simulations. Fureby et al, [138][139], use results from three-dimensional RANS computations by Karl, [132,136], as inflow conditions whereas Larsson, [50], use perturbed RANS predictions as inlet conditions at a more upstream location compared to [132,136].…”

Section: Vid the Hyshot II Combustormentioning

confidence: 98%

“…Fureby et al, [138][139], use results from three-dimensional RANS computations by Karl, [132,136], as inflow conditions whereas Larsson, [50], use perturbed RANS predictions as inlet conditions at a more upstream location compared to [132,136]. Cesare et al, [71], include the full combustor width and all four injectors in their simulation, using 14, 52 and 71 million cells, the FM subgrid flow model and the LES-FFM combustion model using the 1-step reaction mechanism of Marinov et al, [92]. Cesare et al, [71], employ a finite difference based code based on a WENO scheme and a TVD based Runge Kutta time integration algorithm.…”

Section: Vid the Hyshot II Combustormentioning

confidence: 98%

“…A similar approach is the Fractal Flame Model (FFM), [70][71], considering the structure of a turbulent flame as a spectrum of vortices of different scales and chemical compositions, of which only those of size close to λ K may react. This viewpoint is very similar to that of the PaSR model above and that of the Eddy Dissipation Concept (EDC) model, [72].…”

Section: Iiib2 Les Finite Rate Chemistry Modelsmentioning

confidence: 99%

“…Cesare et al, [71], include the full combustor width and all four injectors in their simulation, using 14, 52 and 71 million cells, the FM subgrid flow model and the LES-FFM combustion model using the 1-step reaction mechanism of Marinov et al, [92]. Cesare et al, [71], employ a finite difference based code based on a WENO scheme and a TVD based Runge Kutta time integration algorithm. Fureby et al, [138][139], use two geometries, one with two injectors and one with four injectors, and four grids with 25 and 50, and 50 and 100 million cells, respectively, the MM subgrid flow model and the LES-PaSR combustion model and the 7-step reaction mechanisms of Davidenko, [91].…”

Section: Vid the Hyshot II Combustormentioning

confidence: 99%

“…Due to the wealth of flight test as well as experimental data this case has also been numerically studied by several research groups using RANS, [132][133][134][135][136], hybrid RANS/LES, [137], and LES, [71,50,[138][139]. In this brief summary of LES-based computational activities for the HyShot II combustor we have selected three computational studies, [71,50,[138][139], using similar geometry descriptions, boundary conditions and operating conditions to enable comparison of the different LES methods. Moreover, the most complete RANS published on this case, [132,136], is used as reference.…”

Section: Vid the Hyshot II Combustormentioning

confidence: 99%

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LES for Supersonic Combustion

Fureby

2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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This paper describes the state-of-the-art in Large Eddy Simulation (LES) of supersonic combustion with application to ram and scramjet engines. Some background is provided regarding supersonic combustion with respect to conventional combustion in order to illustrate the complexity facilitated by the supersonic aerothermodynamics. The LES approach is described in some detail, and selected subgrid flow and subgrid combustion models are described. This selection is not comprehensive but rather compiled as to exemplify different classes of models that can and have been used to simulate supersonic combustion. After that chemical kinetics is discussed for hydrogen combustion, and a few examples are provided and compared for a range of reaction mechanisms with increasing complexity. Numerical methods are then briefly discussed in order to provide a sufficiently complete background of the modeling. Based on available results, it appears as if the finite volume method is most common, and thus the emphasis is on this technique. After this overview of the computational machinery selected results are presented and discussed. Results from four different combustor configurations are included, and results from different investigators are described compared. Finally, an attempt is made to provide some guidelines for the future use and development of LES.

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Section: Vid the Hyshot II Combustormentioning

confidence: 98%

Section: Vid the Hyshot II Combustormentioning

confidence: 98%

Section: Iiib2 Les Finite Rate Chemistry Modelsmentioning

confidence: 99%

Section: Vid the Hyshot II Combustormentioning

confidence: 99%

Section: Vid the Hyshot II Combustormentioning

confidence: 99%

See 3 more Smart Citations

LES for Supersonic Combustion

Fureby

2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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Some Aero-Thermodynamics

Bruno

2023

Airbreathing Hypersonic Propulsion

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Large Eddy simulation of turbulent hydrogen-fuelled supersonic combustion in an air cross-flow

2013

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The main aim of this article is to provide a theoretical understanding of the physics of supersonic mixing and combustion. Research in advanced air-breathing propulsion systems able to push vehicles well beyond is of interest around the world. In a scramjet, the air stream flow captured by the inlet is decelerated but still maintains supersonic conditions. As the residence time is very short , the study of an efficient mixing and combustion is a key issue in the ongoing research on compressible flows. Due to experimental difficulties in measuring complex high-speed unsteady flowfields, the most convenient way to understand unsteady features of supersonic mixing and combustion is to use computational fluid dynamics. This work investigates supersonic combustion physics in the Hyshot II combustion chamber within the Large Eddy simulation framework. The resolution of this turbulent compressible reacting flow requires: (1) highly accurate non-dissipative numerical schemes to properly simulate strong gradients near shock waves and turbulent structures away from these discontinuities; (2) proper modelling of the small subgrid scales for supersonic combustion, including effects from compressibility on mixing and combustion; (3) highly detailed kinetic mechanisms (the Warnatz scheme including 9 species and 38 reactions is adopted) accounting for the formation and recombination of radicals to properly predict flame anchoring. Numerical results reveal the complex topology of the flow under investigation. The importance of baroclinic and dilatational effects on mixing and flame anchoring is evidenced. Moreover, their effects on turbulence-scale generation and the scaling law are analysed

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Shock/Boundary Layer/Heat Release Interaction in the HyShot II Scramjet Combustor

Cited by 9 publications

References 17 publications

LES for Supersonic Combustion

LES for Supersonic Combustion

Some Aero-Thermodynamics

Large Eddy simulation of turbulent hydrogen-fuelled supersonic combustion in an air cross-flow

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