A RANS flamelet–progress-variable method for computing reacting flows of real-gas mixtures

Cutrone, Luigi; Palma, P. De; Pascazio, G.; Napolitano, M.

doi:10.1016/j.compfluid.2009.10.001

Cited by 68 publications

(38 citation statements)

References 39 publications

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“…In previous LES studies of this test case, Guézennec et al [19] employed a reduced reaction mechanism accounting for finite-rate chemistry, while Schmitt et al [20] made the assumption of infinitely fast chemistry. This assumption was also made by Cutrone et al [21] as well as by Kim et al [22] who simulated the test case of Singla et al [18] using a Reynolds-averaged Navier-Stokes (RANS) flamelet model. In the present work, we employ the steady laminar flamelet model for LES [23,24] using a presumed β-shape probability density function (PDF) for the subgrid-scale (SGS) fluctuations.…”

Section: Introductionmentioning

confidence: 94%

A flamelet model for transcritical LOx/GCH₄flames

Müller

Pfitzner

2017

J. Phys.: Conf. Ser.

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Abstract. This work presents a numerical framework to efficiently simulate methane combustion at supercritical pressures. A LES flamelet approach is adapted to account for real-gas thermodynamics effects which are a prominent feature of flames at near-critical injection conditions. The thermodynamics model is based on the Peng-Robinson equation of state (PR-EoS) in conjunction with a novel volume-translation method to correct deficiencies in the transcritical regime. The resulting formulation is more accurate than standard cubic EoSs without deteriorating their good computational performance. To consistently account for pressure and strain fluctuations in the flamelet model, an additional enthalpy equation is solved along with the transport equations for mixture fraction and mixture fraction variance. The method is validated against available experimental data for a laboratory scale LOx/GCH 4 flame at conditions that resemble those in liquid-propellant rocket engines. The LES result is in good agreement with the measured OH * radiation. IntroductionTodays main stage liquid-propellant rocket engines (LRE) typically operate at supercritical pressures, i.e., at chamber pressures that exceed the critical pressure of the propellants, and at cryogenic injection temperatures. One or both of the propellants are thus injected at near-critical conditions and mixing, ignition and combustion are affected by non-ideal thermodynamic effects. In particular, the thermodynamic-and transport properties, e.g., density, enthalpy, viscosity, are highly non-linear functions of temperature and pressure. Moreover, the experiments of Mayer et al. [1,2] showed that the surface tension between liquid and vapor is diminished at sufficiently high pressures and mixing is characterized by continuous-phase diffusion rather than by two-phase spray atomization. In these diffusion mixing layers, the fluid properties change drastically and the density may vary by two orders of magnitude within a few micrometers.Such configurations pose a serious challenge for numerical as well as for experimental studies. At the same time, their investigation is important to better understand the involved processes and to develop tools that help in the design of LREs, but also of other high pressure combustion devices, such as novel Diesel motors or gas turbines. The topic received considerable attention in the last decade and several valuable experiments were carried out. Thorough overviews are given, for instance, by Oschwald et al. [5] focusing on the Mascotte testing facility. Along with the better understanding that has been generated by the experimental efforts, several groups developed models and numerical tools to perform simulations of near-critical mixing and combustion allowing for a detailed view on the flow. Among the first to conduct large-eddy simulations (LES) of supercritical injection was Oefelein and Yang [6] and later Zong et al. [7] as well as Oefelein [8]. These studies showed that the accurate treatment of thermodynamic non-idealities are ke...

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Section: Introductionmentioning

confidence: 94%

A flamelet model for transcritical LOx/GCH₄flames

Müller

Pfitzner

2017

J. Phys.: Conf. Ser.

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“…Besides, closure of mean or filtered chemical source terms is still an issue. Cutrone et al 12 showed that the non-premixed flamelet approach is able to simulate the LOx/methane combustion under their working conditions. The present work deals with the large eddy simulation (LES) of a 2D LOx-CH 4 mixing layer.…”

Section: Introductionmentioning

confidence: 99%

LOx/CH4 mixing and combustion under supercritical conditions

Petit

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Turbulent combustion modeling under supercritical conditions is a key issue for the design of liquid rocket engines. In this study we propose to associate a laminar premixed flamelets database (FPI) built under supercritical thermodynamic conditions and a betashape presumed probability density function (PCM) that is depending on the mixture fraction and the progress variable. This modeling strategy (PCM-FPI 1 ) is extended to real gas thermodynamic and applied to a two-dimensional mixing layer where the stream of cold liquid oxygen is counterflowing the hot methane stream. Real gas e↵ects have been validated against NIST data for both methane and oxygen propellants. Laminar supercritical premixed flames exhibit a very low flame speed and thickness, but a very intense flame temperature. The Large-Eddy Simulation of the reacting supercritical mixing layer is performed to assess the soundness of the approach.

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“…The present work reports the validation of a newly developed LES code for the simulation of reactive flows using the FPV model by a comparison with the results obtained using an in-house recently developed RANS solver employing an original SMLD-FPV approach (see references [5,6,7] for the details of the RANS methodology). The flame Sandia D [8] is computed employing two grid densities and the LES code in order to provide a grid sensitivity study on this particular flame.…”

Section: Introductionmentioning

confidence: 99%

LES of the Sandia Flame D Using an FPV Combustion Model

et al. 2015

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The simulation of turbulent combustion phenomena is still an open problem in modern fluid dynamics. Considering the economical importance of hydrocarbon combustion in energy production processes, it is evident the need of an accurate tool with a relatively low computational cost for the prediction of this kind of reacting flows. In the present work, a comparative study is carried out among large eddy simulations, performed with various grid resolutions, a Reynolds averaged Navier-Stokes simulation, and experimental data concerning the well-known Sandia D flame test case. In all the simulations, a flamelet progress variable model has been employed using various hypotheses for the joint probability density function closure. The filtered approach proved to be more accurate than the averaged one, even for the coarser grid used in this work. In fact both approaches have shown poorly accurate predictions in the first part of the combustion chamber, but only by the large eddy simulation one is capable to recover the inlet discrepancies with respect to the experimental data going along the streamwise direction

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A RANS flamelet–progress-variable method for computing reacting flows of real-gas mixtures

Cited by 68 publications

References 39 publications

A flamelet model for transcritical LOx/GCH₄flames

A flamelet model for transcritical LOx/GCH₄flames

LOx/CH4 mixing and combustion under supercritical conditions

LES of the Sandia Flame D Using an FPV Combustion Model

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A RANS flamelet–progress-variable method for computing reacting flows of real-gas mixtures

Cited by 68 publications

References 39 publications

A flamelet model for transcritical LOx/GCH4flames

A flamelet model for transcritical LOx/GCH4flames

LOx/CH4 mixing and combustion under supercritical conditions

LES of the Sandia Flame D Using an FPV Combustion Model

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A flamelet model for transcritical LOx/GCH₄flames

A flamelet model for transcritical LOx/GCH₄flames