Calculation of supersonic turbulent reacting coaxial jets

Eklund, Dean; Drummond, J. P.; Hassan, H. A.

doi:10.2514/3.25262

Cited by 61 publications

(23 citation statements)

References 14 publications

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“…Simultaneous measurement of temperature and species concentration in high speed reacting flow has made the Cheng et al [22,23] experiment very special in supersonic reacting code validation and many authors [18,[24][25][26][27][28][29][30] has taken this experiment a validation case for their numerical studies. In the experiment of Cheng et al [22,23], a pure hydrogen jet is injected at sonic speed into a vitiated supersonic (M a = 2) coflow.…”

Section: Introductionmentioning

confidence: 99%

“…The debate on the use of detailed chemistry vis a vis single step chemistry is not adequately resolved in the literature. Number of finite rate chemistry mechanism including Jachimowski mechanisms from 1988 [13] and 1992 [14], Vajda et al [15], O'Conaire et al [16] and GRI3.0 [17], abridged Spark model [18] etc. are used to predict the H 2 -air reaction in high speed flows.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Dharavath

Manna

Chakraborty

2016

J. Inst. Eng. India Ser. C

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In the present study, the turbulent structure of coaxial supersonic H 2 -air jet is explored numerically by solving three dimensional RANS equations along with two equation k-e turbulence model. Grid independence of the solution is demonstrated by estimating the error distribution using Grid Convergence Index. Distributions of flow parameters in different planes are analyzed to explain the mixing and combustion characteristics of high speed coaxial jets. The flow field is seen mostly diffusive in nature and hydrogen diffusion is confined to core region of the jet. Both single step laminar finite rate chemistry and turbulent reacting calculation employing EDM combustion model are performed to find the effect of turbulencechemistry interaction in the flow field. Laminar reaction predicts higher H 2 mol fraction compared to turbulent reaction because of lower reaction rate caused by turbulence chemistry interaction. Profiles of major species and temperature match well with experimental data at different axial locations; although, the computed profiles show a narrower shape in the far field region. These results demonstrate that standard two equation class turbulence model with single step kinetics based turbulence chemistry interaction can describe H 2 -air reaction adequately in high speed flows.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Dharavath

Manna

Chakraborty

2016

J. Inst. Eng. India Ser. C

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“…A case of detonation is simulated in a mixture of 2H 2 /1O 2 /3Ar initially at a pressure of 26kP a and a temperature of 300K, similar to the experiments of [6]. A 7-steps H 2 /O 2 reaction mechanism is employed to treat the combustion [20], and 500 × 180 × 180 grid cells are used to discretize a physical domain of dimensions 8cm × 1.25cm × 1.25cm. Figure 4.8 shows a snapshot of the detonation structure.…”

Section: Regular and Irregular Cellular Detonationsmentioning

confidence: 99%

Simulation of Compressible Multi-Phase Turbulent Reacting Flows

Menon¹,

Génin²

2008

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Computational Mathematics AFOSR AFOSR/NM 4015 Wilson Blvd, Arlington, VA 22203 SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION / AVAILABILITY STATEMENTUnlimited, Unclassified SUPPLEMENTARY NOTES ABSTRACTSimulation of multi-phase, turbulent reacting flow is in itself a very complex task but when such flows occur in the presence of strong, unsteady shocks additional complexity can arise. Shock interactions with shear turbulence can change turbulent structures and shock induced heating can trigger ignition, combustion and turbulent flame propagation. In this research, a new and an efficient large-eddy simulation (LES) strategy has been developed to investigate turbulent flows in a high-speed, compressible environment. A new numerical algorithm has been validated that permits a proper capture of strong shocks and shear turbulence simultaneously. This algorithm has been combined with a new dynamic subgrid closure for LES of highly compressible flows such that there are no ad hoc adjustable parameters. Extensive validation has been conducted and application of the hybrid solver to shock-shear interactions, re-shocked Richtmyer-Meshkov instability, and regular and irregular detonations have been demonstrated. These results establish a new capability to simulate high Reynolds number complex flows containing strong shocks, shear turbulence and reacting flows in a multi-phase (gas-liquid-solid) environment. SUBJECT TERMSLarge Eddy Simulation, hybrid shock capturing, detonation, shock-shear interactions, Richtmyer-Meshkov instability AFRL Point of ContactDr. Douglas Nance, AFRL/MNAC, Eglin AFB, FL, Phone (850) 883-2684. Regular bi-monthly meetings at Georgia Institute of Technology. Discoveries, inventions, patents None Awards None TransitionsThe code developed and described here has been delivered to AFRL/MNAC for their in-house classified studies of the Agent Defeat problems. Successful application of these codes to practical problems has been demonstrated at Eglin AFB. Classified reports have been submitted by...

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“…Because of its relatively large size, the full version of the J-9S-20R mechanism was only used in the recent LES/RANS study of Edwards (2012, 2014). Based on the J-9S-20R mechanism and invoking the quasi-steady state assumptions to remove the intermediate species HO 2 and H 2 O 2 , Eklund et al (1990) derived a 7-species and 7-reaction reduced mechanism (E-7S-7R), which however contains a non-elementary reaction, H 2 + O 2 → 2OH, to mimic the chain initiation. Both the J-9S-20R and E-7S-7R mechanisms were adopted in the LES/RANS study of Potturi and Edwards (2012), but the predicted flame is detached from the strut, in contradiction with the experimental observation.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Flame Stabilization in DLR Hydrogen Supersonic Combustor with Strut Injection

Zhang

Yao

et al. 2017

Combustion Science and Technology

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Flame stabilization in the DLR hydrogen supersonic combustor with strut injection was numerically investigated by using an in-house large eddy simulation code developed on the OpenFoam platform. To facilitate the comparison and analysis of various hydrogen oxidation mechanisms with different levels of mechanism reduction, the proposed 2D calculation model was validated against both the 3D simulation and the experimental data. The results show that the 2D model can capture the DLR flow and combustion characteristics with satisfactorily quantitative accuracy and significantly less computational load. By virtue of the flow visualization and the analyses of species evolution and heat release, the supersonic combustion in the DLR combustor can be divided into three stages along the streamwise direction: the induction stage where ignition occurs and active radicals are produced, the transition stage through which radicals are advected to the downstream, and the intense combustion stage where most heat release occurs. Furthermore, the sensitivity analysis of key reaction steps identifies the important role of chain carrying and heat release reactions in numerically reproducing the three-stage combustion stabilization mode in the DLR combustor.ARTICLE HISTORY

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Calculation of supersonic turbulent reacting coaxial jets

Cited by 61 publications

References 14 publications

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Simulation of Compressible Multi-Phase Turbulent Reacting Flows

Numerical Investigation on Flame Stabilization in DLR Hydrogen Supersonic Combustor with Strut Injection

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