Computational Combustion

Menon, Suresh; Fureby, Christer

doi:10.1002/9780470686652.eae063

Cited by 20 publications

(23 citation statements)

References 25 publications

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“…The LES model is based on implicitly-filtered transport equations for mass, momentum, energy and species mass-fractions together with thermal and caloric equations-of-state and constitutive equations, [20][21]. The thermal and caloric equations-of-state are obtained under the assumption of a mixture of thermally perfect gases using tabulated formation enthalpies and specific heats.…”

Section: Les Models Numerical Methods and Computational Set-upmentioning

confidence: 99%

A Combined Experimental and Computational Study of the LAPCAT II Supersonic Combustor

Vincent‐Randonnier¹,

Ristori²,

Sabelnikov³

et al. 2018

22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference

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Dual-mode ramjet propulsion systems are suggested for the next generation high-speed flight vehicles. Here, we combine experimental measurements of high-speed (subsonic and supersonic) combustion at different operating conditions in the LAPCAT-II dual-mode ramjet combustor with Large Eddy Simulations (LES) using finite rate chemistry models and new skeletal H 2-air combustion chemistry. The LAPCAT II combustor consists of four sections, and experiments have been performed for wall injection of H 2 in a Ma 2.0 vitiated airflow for total pressures and temperatures of p 0 =0.40 MPa, 1414 K

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Section: Les Models Numerical Methods and Computational Set-upmentioning

confidence: 99%

A Combined Experimental and Computational Study of the LAPCAT II Supersonic Combustor

Vincent‐Randonnier¹,

Ristori²,

Sabelnikov³

et al. 2018

22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference

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“…The total energy  E= ε+ 1 2  v 2 +k is composed of the internal energy  ε=Σ i (  Y i (h i,f θ + C p,i (T)dT T 0  T ∫ ))−p/ρ , the kinetic energy 1 2  v 2 , and the subgrid kinetic energy k. The chemical kinetics of a generic reaction mechanism, P ji r ℑ i ⇔P ji p ℑ i , in which ℑ i represents species i, enters the species equations (1 2 ) by means of the low-pass filtered species reaction rate,  w i =M i P ij  w j , in which  w j =A j T n j e −T A /T Π k=1 N (ρY k ) b k are the Arrhenius reaction rates, P ji =P ji r −P ji p the stoichiometric coefficients, M i the species molar mass, A j the pre-exponential factors, T A,j the activation temperatures, n j the temperature exponent and b j the reaction orders for reaction j. The subgrid flow physics is concealed in the subgrid stress B=ρ(v⊗ṽ − v⊗ v) , and [7,19], that are here modeled by mixed models, [20][21], so that B=ρ(…”

Section: Large Eddy Simulation (Les) Modelmentioning

confidence: 99%

“…LES is based on a separation of scales, which is achieved via spatial lowpass filtering. Physical processes occurring on scales larger than the filter width, ∆, are resolved, whereas physics occurring on scales smaller than ∆ are modeled by subgrid models, [7]. For a linear viscous mixture with Fourier heat conduction and Fickian diffusion the LES equations result from low-pass filtering the reactive flow equations such that,…”

Section: Large Eddy Simulation (Les) Modelmentioning

confidence: 99%

Understanding Scramjet Combustion using LES of the HyShot II Combustor

Zettervall¹,

Nordin-Bates²,

Fureby³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Experimental and flight data for hypersonic air-breathing engines are both difficult and expensive to obtain, motivating the use of computational models to enhance the understanding of the physics involved. Here, a numerical investigation has been carried out for the HyShot II scramjet combustor using Large Eddy Simulation (LES) models together with a skeletal reaction mechanism. Based on a survey of the experimental results available for the HyShot II combustor we focus on the High Enthalpy Shock Tunnel Göttingen (HEG) case XIII, emulating flight conditions at 28 km altitude. To account for the slightly different conditions of the different experimental runs, two simulations at different global equivalence values are performed. The skeletal reaction mechanism used is evaluated against several other reaction mechanisms in order to quantify its accuracy and appropriateness for this type of flows. The LES model is observed to capture the experimental wall-pressure and heat flux data well compared with the measurement data. The LES results are then used to analyze the combined flow, mixing and combustion processes involved. The tools used include conventional as well as recently developed methods such as Takeno Flame Index and Chemical Explosive Model Analysis. These methods give a concise description of the interactions between flow, fuel-air mixing and combustion and it is found that supersonic combustion is a combination of auto-ignition regions, non-premixed flame regions and self-igniting fronts.

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“…Large Eddy Simulation (LES) models, e.g. [5], have been proposed as a promising alternative, having the potential to provide both qualitative and quantitative information about key engine features, in spite of the complex aerothermodynamics involved and the high computational cost of LES. This paper aims at describing the machinery involved in performing LES of supersonic combustion and to present contemporary supersonic combustion LES to exemplify…”

Section: Introductionmentioning

confidence: 99%

LES for Supersonic Combustion

Fureby

2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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This paper describes the state-of-the-art in Large Eddy Simulation (LES) of supersonic combustion with application to ram and scramjet engines. Some background is provided regarding supersonic combustion with respect to conventional combustion in order to illustrate the complexity facilitated by the supersonic aerothermodynamics. The LES approach is described in some detail, and selected subgrid flow and subgrid combustion models are described. This selection is not comprehensive but rather compiled as to exemplify different classes of models that can and have been used to simulate supersonic combustion. After that chemical kinetics is discussed for hydrogen combustion, and a few examples are provided and compared for a range of reaction mechanisms with increasing complexity. Numerical methods are then briefly discussed in order to provide a sufficiently complete background of the modeling. Based on available results, it appears as if the finite volume method is most common, and thus the emphasis is on this technique. After this overview of the computational machinery selected results are presented and discussed. Results from four different combustor configurations are included, and results from different investigators are described compared. Finally, an attempt is made to provide some guidelines for the future use and development of LES.

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Computational Combustion

Cited by 20 publications

References 25 publications

A Combined Experimental and Computational Study of the LAPCAT II Supersonic Combustor

A Combined Experimental and Computational Study of the LAPCAT II Supersonic Combustor

Understanding Scramjet Combustion using LES of the HyShot II Combustor

LES for Supersonic Combustion

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