Simulation of Supersonic Combustion Using Variable Turbulent Prandtl/Schmidt Number Formulation

Keistler, Patrick; Xiao, Xudong; Hassan, H. A.; Rodríguez, Cristian

doi:10.2514/6.2006-3733

Cited by 10 publications

(11 citation statements)

References 30 publications

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“…Baurle and Eklund (2002), for example, discuss scramjet (supersonic combustion ramjet) operation and point out the extreme sensitivity of CFD calculations to the imposed levels of the turbulent Schmidt number: Variations between 0.25 and 0.75, with t Pr =0.89, result in predictions covering the entire range from flame blowout to combustor unstart. Similar evidence is provided in Baurle et al (1998), Yimer et al (2002), Sturgess and McManus (1984), Keistler (2006) and Milligan et al (2010). Several remedies are suggested in the abovementioned references.…”

Section: Introductionsupporting

confidence: 52%

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Variable Turbulent Schmidt and Prandtl Number Modeling

Goldberg

Palaniswamy

Batten

et al. 2010

Engineering Applications of Computational Fluid Mechanics

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This paper describes variable turbulent Schmidt and Prandtl number formulations, based on Rodi's (1980) algebraic Reynolds stress model adapted to velocity-scalar correlations. Since the approach is algebraic in nature, it does not introduce transport equations beyond the ones already existing to compute the flow, rendering it a viable engineering tool. The method is scrutinized against several test cases, including a 3D Scramjet combustor problem. Results are encouraging and lend confidence in the proposed approach.

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Section: Introductionsupporting

confidence: 52%

“…The most elaborate approach is presented in Keistler (2006), where four transport equations are formulated for the enthalpy variance and its dissipation rate (to determine Pr t ) and, similarly, for the mass fraction variance and its dissipation rate (for t Sc ). These partial differential transport equations involve 26 modeling constants.…”

Section: Introductionmentioning

confidence: 99%

Variable Turbulent Schmidt and Prandtl Number Modeling

Goldberg

Palaniswamy

Batten

et al. 2010

Engineering Applications of Computational Fluid Mechanics

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“…Generally speaking, this grid is not accurate enough to capture all fluid dynamics details (e.g., BL transition, or the fine details of SBLI); however, emphasis here is on simulating flame development and anchoring by means of the specially-developed SGS mentioned above. Furthermore, results in [6] for the same combustor and with a similar grid indicate the grid size used is adequate to predict combustor performance. In fact, both the shock departing from the step and that just upstream the fuel injection are well predicted by the simulations performed, leading to the formation of two counter-rotating vortices moving with the stream direction.…”

Section: Computational Domainmentioning

confidence: 88%

Turbulent Combustion Modeling in Supersonic Flows for Future RBCC Vehicles

Ingenito

Bruno

2009

Trans. JSASS Space Tech. Japan

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Mixing and combustion of supersonic reacting flows are currently under investigation for new generation RBCC vehicles. Because of the speed within the SCRJ combustor, the length required for fuel and air to mix and react is commonly thought to be a difficult compromise if friction drag is to be kept to a minimum. LES simulations can be an useful tool to better understand the physics of supersonic combustion. By simulating combustion and analyzing numerical results, it is possible to draw fundamental conclusions suggesting how to design a more efficient combustor. Thus the subgrid scale (SGS) model to be implemented as closure of the filtered Navier Stokes equations is critical in reproducing experimental results and giving credibility to numerical predictions. In the present paper, a new SGS model for supersonic reacting flows is being proposed. This model accounts for compressibility effects on mixing and combustion by introducing a complete equations for the subgrid kinetic energy transport. This equation accounts for the effect of heat release due to combustion, dilatation due to the compressibility of the fluid, and the pressure gradient that are responsible for the baroclinic term and then for streamwise vorticity and dissipation. The reaction rate accounts for the effect of the Mach number by means of the SGS Mach number squared. The effect of the small scales scalars fluctuations on turbulent mass diffusivity is included by modeling the local Schmidt number.

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“…The SCHOLAR experiment was the subject of investigation by the current authors [22][23][24] with limited success. It became evident after thorough investigation that numerical and coding errors were made in previous investigations.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Supersonic Combustion in Three-Dimensional Configurations

Keistler

Hassan

Xiao

2009

Journal of Propulsion and Power

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A turbulence model that calculates the turbulent Prandtl and Schmidt numbers as part of the solution, addresses turbulence/chemistry interactions, and accounts for compressibility effects is used to simulate supersonic combustion in two three-dimensional experiments: the SCHOLAR experiment, which employs vitiated air and hydrogen fuel, and the HyShot experiment, which employs air and hydrogen fuel. Two chemical kinetic models are employed: one employs reaction rates that are functions of temperature, whereas the other employs rates that are both functions of pressure and temperature. In general, fair to good agreement is indicated with available measurements.

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Simulation of Supersonic Combustion Using Variable Turbulent Prandtl/Schmidt Number Formulation

Cited by 10 publications

References 30 publications

Variable Turbulent Schmidt and Prandtl Number Modeling

Variable Turbulent Schmidt and Prandtl Number Modeling

Turbulent Combustion Modeling in Supersonic Flows for Future RBCC Vehicles

Simulation of Supersonic Combustion in Three-Dimensional Configurations

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