A computational study of the HyShot II combustor performance

Chapuis, Michel; Fedina, E.; Fureby, Christer; Hannemann, Klaus; Karl, Sebastian; Schramm, Jan Martinez

doi:10.1016/j.proci.2012.07.014

Cited by 71 publications

(51 citation statements)

References 13 publications

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“…al. [3,10]. In AstroFoam, the flux discretization is extended to second order spatial accuracy by reconstructing the primitive variables on interfaces using Total Variation Diminishing (TVD) scheme, for which the Minmod limiter is used in this study.…”

Section: Solver Setup and Numerical Detailsmentioning

confidence: 99%

“…inlet/isolator, supersonic combustor and expander/nozzle, while modeling of the integrated flow path in a full-scale combustion is generally scarce. From the literature, the most preferred modeling cases are the HyperShot I&II [3][4][5][6][7][8][9][10] and SCHOLAR [11][12][13][14][15][16], due a large degree to their relative complete data on experimental setup and measurements 2 American Institute of Aeronautics and Astronautics for model validation. Simulations based on the experimental cases tested on some other scramjet combustor facilities, such as the DLR scramjet combustor [17,18], the University of Virginia's Supersonic Combustion Facility (SCF) [18][19][20][21] and the CUBRC Combustion Duct [22], are also growing vigorously.…”

Section: Introductionmentioning

confidence: 99%

“…those based on HyperShot I&II [3][4][5][6][7][8][9][10] or SCHOLAR cases [11][12][13][14][15][16], with a few based on pure hydrocarbons (e.g. ethylene [42,72], methane [73,74] and acetone [75]), however few are based kerosene [76][77][78][79].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism

Yao¹,

Wang²,

Lu³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Large Eddy Simulation (LES) of kerosene fueled scramjet combustor is generally scare in the literature, due mainly to the formidable computational cost arisen by complex kerosene mechanism. In this study, the skeletal reduction of a detailed reaction mechanism (2185 species/8217 steps) of aviation kerosene is conducted using directed relation graph with error propagation and sensitivity analysis (DRGEPSA) method, resulting a skeletal mechanism consisting of 39 species/153 elemental reactions for China Daqing RP-3 aviation kerosene. The comparisons of adiabatic flame temperature, total heat release, ignition delay and laminar flame speed predicted by the skeletal mechanism show an overall good accordance with the original detailed reaction mechanism. Then a three-dimensional Detached Eddy Simulation (DES) modeling based on the skeletal kerosene mechanism is employed for the numerical analysis of a full-scale scramjet combustor, which has been experimentally tested in a long-time direct connect supersonic combustion test platform (abbreviated as DTZ) assembled in Chinese Academy of Sciences (CAS). Pressure and heat flux measurement systems are attached to the combustor assembly to monitor the real-time combustion performance and provide validation data for the numerical modeling. Three cases with fuel equivalence ratios from 0.8, 1.0 to 1.2 and the same crossflow conditions at Mach 2.0 are modeled. The time-averaged static pressure and heat flux are in generally good agreement with the experiment with the peak heat flux slightly underpredicted. The instantaneous and/or time-averaged pressure, momentum, temperature and turbulence fields, which are difficult to be measured, are analyzed to reveal the main flow and combustion physics, especially those related to the flame distribution and holding. The combustion is identified as in ramjet mode for the investigated cases. With the increasing of fuel equivalence ratio, the shock train propagates upstream in the isolator and the interaction between the upstream and downstream combustion assumes different patterns.

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Section: Solver Setup and Numerical Detailsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism

Yao¹,

Wang²,

Lu³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…OpenFOAM [16] is a well-established open platform in the scientific community. Supersonic combustion studies with OpenFOAM-based solvers include the work of Chapuis [17], Fureby [18], Dröske [19] and Makowka [20]. Unfortunately the latter OpenFOAM implementations are not yet fully open-source.…”

Section: Introductionmentioning

confidence: 99%

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Hoste

Casseau

Fossati

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

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Two open-source solvers, Eilmer and hyFoam, are here considered for their performance in simulating high-speed flows in different flow conditions and geometric configurations typical of propulsive systems at supersonic speeds. The goal is to identify the open-source platform providing the best compromise between accuracy, flexibility and computational cost to eventually simulate the flow fields inside ramjet and scramjet engines. The differences in terms of discretization and solution methods of the selected solvers are discussed in terms of their impact on solution accuracy and computational efficiency and in view of the aerothermodynamic analysis and design of future transatmospheric propulsive systems. In this work steady state problems are considered. Numerical results of two scramjet type engines demonstrated a similar predictive capability of both codes in non-reacting conditions. These results highlight their potential to be considered for further characterization of overall engine performance. * PhD Candidate, AIAA Student Member. † Lecturer, AIAA Member . ‡ Senior Lecturer.

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“…This methodology was also used to simulate the supersonic reactive flows within the HyShot II scramjet combustor during ground testing in the High Enthalpy Shock Tunnel Göttingen (Fureby, et al, 2011;Chapuis, et al, 2013). The HyShot II combustor is a constant area planar duct with a row of port hole injectors that face normal to the bottom duct wall surface.…”

Section: Computational Fluid Dynamics 49mentioning

confidence: 99%

Flow physics of a hypervelocity mixing wake with oxygen enrichment

Petty¹

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A computational study of the HyShot II combustor performance

Cited by 71 publications

References 13 publications

Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism

Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Flow physics of a hypervelocity mixing wake with oxygen enrichment

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