An Implicit Multigrid Method for Turbulent Combustion

Gerlinger, Peter; Möbus, H.; Brüggemann, Dieter

doi:10.1006/jcph.2000.6671

Cited by 99 publications

(52 citation statements)

References 35 publications

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“…The forward and backward reaction rates are computed using the modi¦ed Arrhenius law and equilibrium constants. Turbulencechemistry interactions are modeled using an assumed probability density function (PDF) approach [18] which considers local §uctuation of temperature and species concentrations. Two sets of reaction mechanisms for hydrogen combustion were considered: a 19-step [18] and a reduced 7-step [19] mechanism based on the Jachimowski scheme.…”

Section: Dlr Tau Codementioning

confidence: 99%

“…Turbulencechemistry interactions are modeled using an assumed probability density function (PDF) approach [18] which considers local §uctuation of temperature and species concentrations. Two sets of reaction mechanisms for hydrogen combustion were considered: a 19-step [18] and a reduced 7-step [19] mechanism based on the Jachimowski scheme. A detailed model description and performance assessment for steady and unsteady combustion problems is given in [20,21].…”

Section: Dlr Tau Codementioning

confidence: 99%

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Investigation of different modeling approaches for computational fluid dynamics simulation of high-pressure rocket combustors

Ivancic

Riedmann

Frey

et al. 2016

Progress in Propulsion Physics

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Section: Dlr Tau Codementioning

confidence: 99%

Section: Dlr Tau Codementioning

confidence: 99%

Investigation of different modeling approaches for computational fluid dynamics simulation of high-pressure rocket combustors

Ivancic

Riedmann

Frey

et al. 2016

Progress in Propulsion Physics

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“…However, recent work has shown the limitations of RANS methods when it comes to predicting the wall heat §ux in a model rocket combustor with shear coaxial injectors [13].…”

Section: Introductionmentioning

confidence: 99%

Assumed PDF modeling in rocket combustor simulations

Lempke

Gerlinger

Aigner

2013

Progress in Propulsion Physics

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In order to account for the interaction between turbulence and chemistry, a multivariate assumed PDF (Probability Density Function) approach is used to simulate a model rocket combustor with ¦nite-rate chemistry. The reported test case is the PennState preburner combustor with a single shear coaxial injector. Experimental data for the wall heat §ux is available for this con¦guration. Unsteady RANS (Reynolds-averaged NavierStokes) simulation results with and without the assumed PDF approach are analyzed and compared with the experimental data. Both calculations show a good agreement with the experimental wall heat §ux data. Signi¦cant changes due to the utilization of the assumed PDF approach can be observed in the radicals, e. g., the OH mass fraction distribution, while the e¨ect on the wall heat §ux is insigni¦cant.

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“…A constant turbulent Schmidt number Sc t = 0.80 and laminar/turbulent Pr ratio of 0.8 were assumed. Combustion was modeled by the modi¦ed 9 species (N 2 , O 2 , H 2 , H 2 O, OH, O, H, HO 2 , and H 2 O 2 ), 19-step chemical kinetics model of Jachimowski [11], where nitrogen reactions and turbulence chemistry interactions were ignored [12,13].…”

Section: Numerical Setupmentioning

confidence: 99%

Numerical investigation of a hydrogen-fueled scramjet combustor at flight conditions

Rabadan

2013

Progress in Propulsion Physics

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Numerical investigations of a hydrogen-fueled scramjet combustor at cruise §ight conditions of Mach 8 at an altitude of 30 km have been performed. Two combustor con¦gurations were investigated: a single-stage combustor with a central strut injector and a two-staged combustor combining the central strut and wall-mounted ramp injectors. These numerical simulations are aimed to study the §ow structure, supersonic mixing, autoignition, and combustion for the present combustor con¦gurations. A turbulent §ow from a separate intake calculation was used as in §ow condition for the combustor. A better performance for the two-staged combustor con¦guration was observed. The combination of the central strut injection together with the wall-ramp injection improved the turbulent mixing and, consequently, the combustion process. Inside the supersonic combustion chamber, the autoignition zone occurred downstream of the injectors, and combustion takes place accompanied by high heat release and pressure rise. As the equivalence ratio was increased, the combustion became stronger causing an upstream displacement of the shock train producing di¨erent pressure variations. For the two-staged combustor con¦guration, the location of the autoignition zone was found to appear further upstream compared to single-stage combustor. Mixing was improved by addition of the second-stage injection. The in §uence of the wall temperature was also investigated showing an e¨ect on the combustion pressure rise and the length and location of the shock train.

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An Implicit Multigrid Method for Turbulent Combustion

Cited by 99 publications

References 35 publications

Investigation of different modeling approaches for computational fluid dynamics simulation of high-pressure rocket combustors

Investigation of different modeling approaches for computational fluid dynamics simulation of high-pressure rocket combustors

Assumed PDF modeling in rocket combustor simulations

Numerical investigation of a hydrogen-fueled scramjet combustor at flight conditions

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