Scalar Fluctuation and Transport Modeling for Application to High Speed Reacting Flows

Calhoon, William H.; Brinckman, Kevin; Tomes, Jeremy; Mattick, Stephen J.; Dash, S. M.

doi:10.2514/6.2006-1452

Cited by 16 publications

(6 citation statements)

References 15 publications

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“…The first studies were carried out by J. Evans et al and are presented in [3][4]. These data are widely used for the validation of CFD programs so far -e.g., [4,[13][14][15][16][17][18]. In these experiments, pressure measurements were made by the Pitot tube and sampling of gas followed by concentrations measurement.…”

Section: Introductionmentioning

confidence: 99%

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Critical analysis of classical turbulent combustion experiments on the basis of RANS simulations

Shiryaeva

Sabelnikov

2018

AIP Conference Proceedings

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The purpose of the work is to analyze the consistency of experimental data concerning classical turbulent combustion tests and their applicability for CFD programs validation. Efforts are directed to development and verification of a computationally efficient method for numerical simulation of turbulent combustion in a high-speed flow, based on RANS equations and taking into account turbulence-combustion interaction (TCI). Computations are fulfilled with zFlare module from application package EWT-TsAGI [1] which is based on in-house code ZEUS (TsAGI) [2] and intended to describe the flows of ideal compressible gases mixtures with variable heat capacities and nonequilibrium chemical reactions. Several kinetics models for H2 and hydrocarbon fuel combustion in air together with two-parameter turbulence models based on the Boussinesq hypothesis are implemented into the program. The paper describes some results of zFlare verification, as well as detailed analyses of experimental data. Five classical turbulent combustion experiments are regarded: Evans et al. experiments [3-4], Burrows & Kurkov [5], A.D.Cutler [6-7], Cheng et al. [8] and Moreau et al. backward-facing step combustor [9]. In addition, several approaches for TCI based on methods of Partially Stirred Reactor model (PaSR, [10]) have been studied and compared.

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Section: Introductionmentioning

confidence: 99%

“…In these experiments visual methods were used to measure temperature and concentration: spontaneous Raman scattering (SRS) and laser induced fluorescence (LIF). This work is very widely used now for CFD programs validation -e.g., [12,[18][19][20][21][22]. Both measurement technologies are based on the detection of incoherent light.…”

Section: Introductionmentioning

confidence: 99%

Critical analysis of classical turbulent combustion experiments on the basis of RANS simulations

Shiryaeva

Sabelnikov

2018

AIP Conference Proceedings

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“…For variable composition jet/mixing problems, the SFM solves PDE's for species variance and dissipation rates comparable to those used for predicting energy/ temperature fluctuations. It has been utilized for analyzing helium/hydrogen/ hydrocarbon jets and varied fuel/air mixing problems with and without combustion [15,16]. In the practical application of this model, we have used a lumped twoparameter species approach (rather than analyzing all the chemical species), with the solution of the species PDE's and time-scale relations providing the distribution of the turbulent Schmidt number in the flow.…”

Section: Introduction and Historical Perspectivementioning

confidence: 99%

Turbulence Modeling Advances and Validation for High Speed Aeropropulsive Flows

Dash

Brinckman

Ott

2012

International Journal of Aeroacoustics

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Advances made in extending a unified k-ε based RANS turbulence model to "more reliably" analyze high-speed aero-propulsive flows are discussed. The unified model solves additional scalar fluctuation model (SFM) equations to predict variations in turbulent Prandtl and Schmidt numbers, which can be quite substantial for these types of flows. The discussion includes a historical perspective of the developmental work performed as well as an overview of the current modeling status. RANS modeling still plays a dominant role in the "practical" analysis of aeropropulsive flows. It is used for preliminary design and design-optimization studies, where a large matrix of calculations must be performed, and, in the application of hybrid RANS/LES methodology, where the use of LES is often restricted to massively separated or jet/free shear regions of the flow. In extending the model, we have adhered to a "building-block" philosophy using data sets of increasing complexity and emphasizing high-speed applications where compressibility effects can play a dominant role. Fundamental laboratory data sets as well as benchmark LES/DNS solutions have been used for model calibration and validation, with several key comparisons presented in this article. Recent extensions described in this article include: low Re extensions to the SFM model improving near wall predictions; a compressibility/density gradient correction to the species fluctuation equation improving mixing predictions; and, a baroclinic torque correction to the kinetic energy equation improving predictions for angled jets. This article shows how these extensions serve to improve comparisons with data for a number of basic aeropropulsive flows, and it also discusses utilization of the unified RANS model in a hybrid RAN/LES DES modeling framework. NOMENCLATURE CC Compressibility correction nomenclature CVS Compressible vortex stretching nomenclature DES Detached Eddy Simulation DNS Direct Numerical Simulation EASM Explicit Algebraic Stress Model F d Density correction term in k f equation F m , f 1 , f 2 Near wall damping terms in SSGZ model G b Baroclinic torque correction term in k equation k Turbulent kinetic energy (TKE) k e Internal energy (or temperature) variance k f Species variance L et Turbulent Lewis number LES Large Eddy Simulation M Mach number M c Convective Mach number M t Turbulent Mach number PDE Partial differential equation P k Turbulent production term Pr t Turbulent Prandtl Number RANS Reynolds averaged Navier-Stokes SSGZ So, Sarkar, Gerodimos, and Zhang Sc t Turbulent Schmidt Number SFM Scalar fluctuation model SS ε Round jet vortex stretching correction SS k Compressibility correction term SWBLI Shock wave boundary layer interaction ε Dissipation rate of turbulent kinetic energy ε e Dissipation rate of internal energy fluctuations ε f Dissipation rate of scalar fluctuations λ b Near wall coefficient blending function ξ εT Near wall damping term in SFM model µ t Turbulent viscosity 814 Turbulence modeling advances and validation for high speed aeropropul...

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“…Sarkar [1991] conducted a scaling analysis based on the decomposition of the pressure field into contributions of incompressible and purely compressible components, and found from DNS studies of isotropic compressible turbulence (Sarkar [1991]) and compressible shear flows (Sarkar [1992]) that the pressure-dilatation scales as: where Skk represents the flow dilatation. This model is still used in some RANS applications (Calhoon et al [2006], Fasel et al [2006]) In practical aerodynamics flows, this correlation was found from asymptotic analysis to be a function of the departure from equilibrium of the turbulent kinetic energy budget. Ristorcelli [1997] found that:…”

Section: Turbulence Modeling For Compressible and High-speed Flowsmentioning

confidence: 99%

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

Menon¹,

Génin²

2009

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REPORT DOCUMENTATION PAGEThe 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 the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the 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 0MB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) 28-02-2009 2. REPORT TYPE Final Report DATES COVERED {From -To)December 1 PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)School of Aerospace Engineering Georgia Institute of Technology Atlanta, GA 30332 PERFORMING ORGANIZATION REPORT NUMBERCCL-TR-2009-02-1 SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)AFOSR/NL 4015 Wilson Blvd ? Arlington, VA 22203 Dr. Fariba Fahroo SPONSOR/MONITORS ACRONYM(S)AFOSR/NM SPONSOR/MONITORS REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTUnlimited, Unclassified SUPPLEMENTARY NOTES ABSTRACTA Large-Eddy Simulation (LES) methodology adapted to the resolution of high Reynolds number turbulent flows in supersonic conditions was proposed and developed. A novel numerical scheme was designed, that switches from a low-dissipation central scheme for turbulence resolution to a flux difference splitting scheme in regions of discontinuities. A state-of-the-art closure model was extended in order to take compressibility effects and the action of shock / turbulence interaction into account. The proposed method was validated and employed for the study of shock / turbulent shear layer interaction as a mixing-augmentation technique, and highlighted the efficiency in mixing improvement after the interaction, but also the limited spatial extent of this turbulent enhancement. A second study focused on the injection of a sonic jet normally to a supersonic crossflow. The validity of the simulation was assessed by comparison with experimental data, and the dynamics of the interaction was examined. The sources of vortical structures were identified, with a particular emphasis on the impact of the flow speed onto the vortical evolution. It is shown that the developed hybrid methodology permits a capture of shock / turbulence interactions in direct simulations that agrees well with other reference simulations, and that the LES methodology effectively reproduces the turbulence evolution and physical phenomena involved in the interaction. This numerical approach is then employed to study a problem of practical importance in high-speed mixing. The inter...

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Scalar Fluctuation and Transport Modeling for Application to High Speed Reacting Flows

Cited by 16 publications

References 15 publications

Critical analysis of classical turbulent combustion experiments on the basis of RANS simulations

Critical analysis of classical turbulent combustion experiments on the basis of RANS simulations

Turbulence Modeling Advances and Validation for High Speed Aeropropulsive Flows

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

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