A Priori Analysis of Flamelet-based Modeling for a Dual-Mode Scramjet Combustor

Quinlan, Jesse R.; McDaniel, James C.; Drozda, Tomasz G.; Lacaze, Guilhem; Oefelein, Joseph C.

doi:10.2514/6.2014-3743

Cited by 18 publications

(10 citation statements)

References 30 publications

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“…Data sampled from between the fuel injectors (lighter symbols) suggest a more consistent transition to burning, as hot air is entrained with burning gases in this highly unsteady region. Profiles with similar flame structure and temperature range have been reported in previous RANS [33] and LES [25] studies of this configuration.…”

Section: Analysis and Discussionsupporting

confidence: 59%

Large eddy simulations of the HIFiRE scramjet using a compressible flamelet/progress variable approach

Saghafian

Shunn

Philips

et al. 2015

Proceedings of the Combustion Institute

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In this study, large eddy simulations (LES) of supersonic combustion using a compressible flamelet/progress variable (CFPV) approach are performed for the HIFiRE scramjet at Mach 8 flight conditions. The LES results show good agreement with the ground test experimental measurements. The combustion model is based on an efficient flamelet approach, where compressibility corrections are devised based on assumed functional forms of important thermo-chemical quantities. Specifically, the source term of the progress variable is rescaled with the local density and temperature in the LES, leading to improved predictions relative to existing flamelet models. A modified equilibrium wall-model, capable of predicting the viscous heating, is used in the viscous near-wall region. Temperature near the wall increases significantly due to viscous heating, enhancing the reaction rate and heat-release. This is shown to be a crucial step for accurately predicting the pressure rise in the combustor.

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Section: Analysis and Discussionsupporting

confidence: 59%

Large eddy simulations of the HIFiRE scramjet using a compressible flamelet/progress variable approach

Saghafian

Shunn

Philips

et al. 2015

Proceedings of the Combustion Institute

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“…This clearly illustrates the need to examine alternative methods that accurately parameterize complex chemistry with only a limited number of scalars. Our group is currently examining a flamelet-based strategy [34,35] to address this issue.…”

Section: Combusting Resultsmentioning

confidence: 99%

Hybrid Reynolds-Averaged/Large-Eddy Simulation of a Scramjet Cavity Flameholder

Baurle

2017

AIAA Journal

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.J055339Steady-state and scale-resolving simulations have been performed for flow in and around a model scramjet combustor flameholder. Experimental data available for this configuration include velocity statistics obtained from particle image velocimetry as well as a limited number of scalar measurements using laser-induced breakdown spectroscopy. Several turbulence models were used for the steady-state Reynolds-averaged simulations, which included both linear and nonlinear eddy viscosity models. The scale-resolving simulations used a hybrid Reynoldsaveraged/large-eddy simulation strategy that is designed to be a large-eddy simulation everywhere except in the inner portion (log layer and below) of the boundary layer. Hence, this formulation can be regarded as a wall-modeled largeeddy simulation. This effort was undertaken to not only assess the performance of the hybrid Reynolds-averaged/ large-eddy simulation modeling approach in a flowfield of interest to the scramjet research community but also to begin to understand how this capability can best be used to augment standard Reynolds-averaged simulations. The numerical errors were quantified for the steady-state simulations and at least qualitatively assessed for the scaleresolving simulations before making any claims of predictive accuracy relative to the measurements. The steady-state Reynolds-averaged results displayed a high degree of variability when comparing the flameholder fuel distributions obtained from each turbulence model. This prompted the consideration of applying the higher-fidelity scale-resolving simulations as a surrogate "truth" model to calibrate the Reynolds-averaged closures in a nonreacting setting before their use for the combusting simulations. In general, the Reynolds-averaged velocity profile predictions at the lowest fueling level matched the particle imaging measurements almost as well as was observed for the nonreacting condition. However, the velocity field predictions proved to be more sensitive to the flameholder fueling rate than was indicated in the measurements.

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“…Previous analysis of the HDCR combustor suggested the combustion data was characterized by a wide range of Damköhler number, which thereby supports the existence of strong finite-rate effects. 10 For this reason, it was important to confirm that the FPV models and accompanying flamelet libraries included flamelet solutions along the unstable burning branch of the S-schaped curve, in addition to those along the mixing line and the branch of stable burning solutions. Without the inclusion of the unstable branch, transition from a burning state to the mixing line is non-physical, as demonstrated in Fig.…”

Section: Iic Flamelet Table Generationmentioning

confidence: 99%

“…These p levels were chosen to best represent the extent of pressure variation observed in the baseline RANS data of the HDCR for dual-mode operation. 10 At each p level, the solutions were parameterized by χ st , resulting in a complete parameterization using Z, χ st , and p, thereby yielding a three-dimensional state-space. Again, for FT2, the fuel and oxidizer temperatures were held constant at 300K and 1100K, respectively.…”

Section: Iic Flamelet Table Generationmentioning

confidence: 99%

“…9 This study builds upon a previously-reported a priori analysis of the HDCR data. 10,11 Within the proposed APFM-RANS analysis, a flamelet table is first constructed by solving the flamelet equations and is subsequently parameterized by a small set of tracking scalars, including mixture fraction, progress variable, and other scalars depending upon the flamelet model formulation. These tracking scalars of interest are computed from the RANS simulations of the HDCR that utilized finite-rate chemical kinetics and are then used to retrieve other necessary thermochemical data from the flamelet table.…”

Section: Introductionmentioning

confidence: 99%

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A Priori Analysis of a Compressible Flamelet Model using RANS Data for a Dual-Mode Scramjet Combustor

Quinlan

Drozda

McDaniel

et al. 2015

22nd AIAA Computational Fluid Dynamics Conference

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In an effort to make large eddy simulation of hydrocarbon-fueled scramjet combustors more computationally accessible using realistic chemical reaction mechanisms, a compressible flamelet/progress variable (FPV) model was proposed that extends current FPV model formulations to high-speed, compressible flows. Development of this model relied on observations garnered from an a priori analysis of the Reynolds-Averaged Navier-Stokes (RANS) data obtained for the Hypersonic International Flight Research and Experimentation (HIFiRE) dual-mode scramjet combustor. The RANS data were obtained using a reduced chemical mechanism for the combustion of a JP-7 surrogate and were validated using available experimental data. These RANS data were then post-processed to obtain, in an a priori fashion, the scalar fields corresponding to an FPV-based modeling approach. In the current work, in addition to the proposed compressible flamelet model, a standard incompressible FPV model was also considered. Several candidate progress variables were investigated for their ability to recover static temperature and major and minor product species. The effects of pressure and temperature on the tabulated progress variable source term were characterized, and model coupling terms embedded in the Reynoldsaveraged Navier-Stokes equations were studied. Finally, results for the novel compressible flamelet/progress variable model were presented to demonstrate the improvement attained by modeling the effects of pressure and flamelet boundary conditions on the combustion.

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A Priori Analysis of Flamelet-based Modeling for a Dual-Mode Scramjet Combustor

Cited by 18 publications

References 30 publications

Large eddy simulations of the HIFiRE scramjet using a compressible flamelet/progress variable approach

Large eddy simulations of the HIFiRE scramjet using a compressible flamelet/progress variable approach

Hybrid Reynolds-Averaged/Large-Eddy Simulation of a Scramjet Cavity Flameholder

A Priori Analysis of a Compressible Flamelet Model using RANS Data for a Dual-Mode Scramjet Combustor

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