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Journal articles on the topic 'Combustion Simulations'

Author: Grafiati

Published: 6 September 2023

Last updated: 31 July 2025

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1

Rowan, Steven L., Ismail B. Celik, Albio D. Gutierrez, and Jose Escobar Vargas. "A Reduced Order Model for the Design of Oxy-Coal Combustion Systems." Journal of Combustion 2015 (2015): 1–9. http://dx.doi.org/10.1155/2015/943568.

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Oxy-coal combustion is one of the more promising technologies currently under development for addressing the issues associated with greenhouse gas emissions from coal-fired power plants. Oxy-coal combustion involves combusting the coal fuel in mixtures of pure oxygen and recycled flue gas (RFG) consisting of mainly carbon dioxide (CO2). As a consequence, many researchers and power plant designers have turned to CFD simulations for the study and design of new oxy-coal combustion power plants, as well as refitting existing air-coal combustion facilities to oxy-coal combustion operations. While C

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2

Li, Zhongwen, Jingbo Wang, and Xiangyuan Li. "Combustion simulations of scramjet combustor using reduced mechanism of surrogate fuel for regenerative cooling pyrolysis products." Thermal Science, no. 00 (2024): 114. http://dx.doi.org/10.2298/tsci231223114l.

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Taking the surrogate fuel (64% ethylene and 36% methane in mole percentage) for regenerative cooling pyrolysis products used in HIFiRE-2 scramjet combustor as an example, present work systematically explores the workflow of the integrated mechanism reduction for surrogate fuel of pyrolysis products, the kinetic performance verification of the preferred reduced mechanism, and the combustion simulation application of the reduced mechanism in scramjet combustor. A static integrated reduction strategy is performed to obtain reduced mechanism for the surrogate fuel with the NUIGMech1.2 as detailed

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3

Åkerblom, Arvid, Francesco Pignatelli, and Christer Fureby. "Numerical Simulations of Spray Combustion in Jet Engines." Aerospace 9, no. 12 (2022): 838. http://dx.doi.org/10.3390/aerospace9120838.

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The aviation sector is facing a massive change in terms of replacing the currently used fossil jet fuels (Jet A, JP5, etc.) with non-fossil jet fuels from sustainable feedstocks. This involves several challenges and, among them, we have the fundamental issue of current jet engines being developed for the existing fossil jet fuels. To facilitate such a transformation, we need to investigate the sensitivity of jet engines to other fuels, having a wider range of thermophysical specifications. The combustion process is particularly important and difficult to characterize with respect to fuel chara

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Sikorski, K., Kwan Liu Ma, Philip J. Smith, and Bradley R. Adams. "Distributed combustion simulations." Energy & Fuels 7, no. 6 (1993): 902–5. http://dx.doi.org/10.1021/ef00042a029.

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5

Pries, Michael, Andreas Fiolitakis, and Peter Gerlinger. "Numerical Investigation of a High Momentum Jet Flame at Elevated Pressure: A Quantitative Validation with Detailed Experimental Data." Journal of the Global Power and Propulsion Society 4 (December 18, 2020): 264–73. http://dx.doi.org/10.33737/jgpps/130031.

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The development of efficient low emission combustion systems requires methods for an accurate and reliable prediction of combustion processes. Computational Fluid Dynamics (CFD) in combination with combustion modelling is an important tool to achieve this goal. For an accurate computation adequate boundary conditions are crucial. Especially data for the temperature distribution on the walls of the combustion chamber are usually not available. The present work focuses on numerical simulations of a high momentum jet flame in a single nozzle FLOX® type model combustion chamber at elevated pressur

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6

Tamanampudi, Gowtham Manikanta Reddy, Swanand Sardeshmukh, William Anderson, and Cheng Huang. "Combustion instability modeling using multi-mode flame transfer functions and a nonlinear Euler solver." International Journal of Spray and Combustion Dynamics 12 (January 2020): 175682772095032. http://dx.doi.org/10.1177/1756827720950320.

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Modern methods for predicting combustion dynamics in high-pressure combustors range from high-fidelity simulations of sub-scale model combustors, mostly for validation purposes or detailed investigations of physics, to linearized, acoustics-based analysis of full-scale practical combustors. Whereas the high-fidelity simulations presumably capture the detailed physics of mixing and heat addition, computational requirements preclude their application for practical design analysis. The linear models that are used during design typically use flame transfer functions that relate the unsteady heat a

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Sehole, Hafiz Ali Haider, Ghazanfar Mehdi, Rizwan Riaz, and Adnan Maqsood. "Investigation of Sustainable Combustion Processes of the Industrial Gas Turbine Injector." Processes 13, no. 4 (2025): 960. https://doi.org/10.3390/pr13040960.

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This study investigates the combustion dynamics of methane in a dual swirl combustor, focusing on improving combustion efficiency and understanding flow features. Methane, as a conventional fuel, offers high energy content and relatively low carbon emissions compared to other hydrocarbons, making it a promising choice for sustainable energy solutions. Accurate numerical models are essential for the optimization of combustion processes, particularly in the design of combustion engines utilizing methane. In this work, we employ a partially premixed combustion model based on a mixture fraction an

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8

Fooladgar, Ehsan, and C. K. Chan. "Large Eddy Simulation of a Swirl-Stabilized Pilot Combustor from Conventional to Flameless Mode." Journal of Combustion 2016 (2016): 1–16. http://dx.doi.org/10.1155/2016/8261560.

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This paper investigates flame and flow structure of a swirl-stabilized pilot combustor in conventional, high temperature, and flameless modes by means of a partially stirred reactor combustion model to provide a better insight into designing lean premixed combustion devices with preheating system. Finite rate chemistry combustion model with one step tuned mechanism and large eddy simulation is used to numerically simulate six cases in these modes. Results show that moving towards high temperature mode by increasing the preheating level, the combustor is prone to formation of thermalNOxwith hig

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9

Thelen, Bryce C., and Elisa Toulson. "A computational study on the effect of the orifice size on the performance of a turbulent jet ignition system." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 231, no. 4 (2016): 536–54. http://dx.doi.org/10.1177/0954407016659199.

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Fully three-dimensional computational fluid dynamic simulations with detailed combustion chemistry of a turbulent jet ignition system installed in a rapid compression machine are presented. The turbulent jet ignition system is a prechamber-initiated combustion system intended to allow lean-burn combustion in spark ignition internal-combustion engines. In the presented configuration, the turbulent jet ignition prechamber has a volume that is 2% of the volume of the main combustion chamber in the rapid compression machine and is separated from the main chamber by a nozzle containing a single ori

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10

Meng, Nan, and Feng Li. "Large-Eddy Simulations of Unsteady Reaction Flow Characteristics Using Four Geometrical Combustor Models." Aerospace 10, no. 2 (2023): 147. http://dx.doi.org/10.3390/aerospace10020147.

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Combustion instability constitutes the primary loss source of combustion chambers, gas turbines, and aero engines, and it affects combustion performance or results in a sudden local oscillation. Therefore, this study investigated the factors affecting flame fluctuation on unsteady combustion flow fields through large-eddy simulations. The effects of primary and secondary holes in a triple swirler staged combustor on flame propagation and pressure fluctuation in a combustion field were studied. Moreover, the energy oscillations and dominant frequencies in the combustion field were obtained usin

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11

Zhang, Linqing, Juntao Chang, Wenxiang Cai, Hui Sun, and Yingkun Li. "A Preliminary Research on Combustion Characteristics of a Novel-Type Scramjet Combustor." International Journal of Aerospace Engineering 2022 (December 30, 2022): 1–18. http://dx.doi.org/10.1155/2022/3930440.

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In this work, a new configuration of strut-based scramjet is proposed, and a series of simulations are conducted to investigate its possibility of practical application. The simulation results are verified via the classical DLR ramjet and an experiment conducted on the connected pipe facility. The inlet area ( A in ) and air intake height ( H ) of the combustor are varied independently to investigate their performance. The results indicate that the flow field and shock wave structure of such engine reveal similar characteristics as the classical DLR engine, and the variation in engine geometry

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12

Rao, M. Srinivasa. "Flow Analyses of Integrated Liquid Fuel RAMJET Propulsion System." Defence Science Journal 74, no. 2 (2024): 288–92. http://dx.doi.org/10.14429/dsj.74.18510.

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A CFD study is performed to check the seamless flow behaviour of the Liquid Fuel Ramjet Propulsion system which includes, air intakes, combustor and nozzle. Resolving both supersonic and subsonic flow scales in the same domain makes the simulations complex. Addition of combustion with stiff chemistry makes the simulations more difficult. CFD simulations are carried out using commercially available CFD software. Liquid fuel is injected as discrete phase and the flow turbulence is modelled using Realizable k-ε turbulence model. Jet-A + air combustion has been simulated using combined finite rate

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13

Liu, Hao, Wen Yan Song, and Shun Hua Yang. "Large Eddy Simulation of Hydrogen-Fueled Supersonic Combustion with Strut Injection." Applied Mechanics and Materials 66-68 (July 2011): 1769–73. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.1769.

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In order to obtain more accurate simulation results and properties of combustion in supersonic combustion flow fields, modules of large eddy simulation of reactive turbulent flow and fifth-order WENO scheme was developed. Large eddy simulation of hydrogen-fueled supersonic combustion with strut injection was conducted. Simulations results compare were with experimental measurements, which including wall pressure, velocity, velocity fluctuation and temperature.

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14

Chambers, Steven, Horia Flitan, Paul Cizmas, Dennis Bachovchin, Thomas Lippert, and David Little. "The Influence of In Situ Reheat on Turbine-Combustor Performance." Journal of Engineering for Gas Turbines and Power 128, no. 3 (2004): 560–72. http://dx.doi.org/10.1115/1.2135812.

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This paper presents a numerical and experimental investigation of the in situ reheat necessary for the development of a turbine-combustor. The flow and combustion were modeled by the Reynolds-averaged Navier-Stokes equations coupled with the species conservation equations. The chemistry model used herein was a two-step, global, finite rate combustion model for methane and combustion gases. A numerical simulation was used to investigate the validity of the combustion model by comparing the numerical results against experimental data obtained for an isolated vane with fuel injection at its trail

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15

Mahesh, K., G. Constantinescu, S. Apte, G. Iaccarino, F. Ham, and P. Moin. "Large-Eddy Simulation of Reacting Turbulent Flows in Complex Geometries." Journal of Applied Mechanics 73, no. 3 (2005): 374–81. http://dx.doi.org/10.1115/1.2179098.

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Large-eddy simulation (LES) has traditionally been restricted to fairly simple geometries. This paper discusses LES of reacting flows in geometries as complex as commercial gas turbine engine combustors. The incompressible algorithm developed by Mahesh et al. (J. Comput. Phys., 2004, 197, 215–240) is extended to the zero Mach number equations with heat release. Chemical reactions are modeled using the flamelet/progress variable approach of Pierce and Moin (J. Fluid Mech., 2004, 504, 73–97). The simulations are validated against experiment for methane-air combustion in a coaxial geometry, and j

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16

Zhu, Zhouyuan, Canhua Liu, Yajing Chen, Yuning Gong, Yang Song, and Junshi Tang. "In-situ Combustion Simulation from Laboratory to Field Scale." Geofluids 2021 (December 14, 2021): 1–12. http://dx.doi.org/10.1155/2021/8153583.

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In-situ combustion simulation from laboratory to field scale has always been challenging, due to difficulties in deciding the reaction model and Arrhenius kinetics parameters, together with erroneous results observed in simulations when using large-sized grid blocks. We present a workflow of successful simulation of heavy oil in-situ combustion process from laboratory to field scale. We choose the ongoing PetroChina Liaohe D block in-situ combustion project as a case of study. First, we conduct kinetic cell (ramped temperature oxidation) experiments, establish a suitable kinetic reaction model

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17

Rashkovskiy, Sergey. "Simulation of Gasless Combustion of Mechanically Activated Solid Powder Mixtures." Advances in Science and Technology 63 (October 2010): 213–21. http://dx.doi.org/10.4028/www.scientific.net/ast.63.213.

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The direct 3D method of numerical simulation of gasless combustion of mechanically activated solid powder mixtures is developed. The method under consideration falls into three stages. On the first stage, a simulation of mixture structure is performed. An analysis of the structure obtained in simulations is carried out. On the second stage, the thermal conductivity of solid powder mixture is calculated. On the third stage of simulation, the ignition and combustion of each particle of the mixture is considered with taking into account of heat exchange between contacting particles. The results o

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18

Lee, Jaeyoung, Chang Bum Sohn, Young Sik Jeong, and Young Bae Kim. "A Numerical Analysis of Premixed Hydrogen–Methane Flame with Three Different Header Types of Combustor." Fire 7, no. 10 (2024): 361. http://dx.doi.org/10.3390/fire7100361.

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This study investigated the impact of thin-flame combustor design on hydrogen flame characteristics and combustion performance through numerical simulations. Differences in the flame shape and combustibility between pure methane and pure hydrogen combustion were analyzed. Three combustor header shapes (flat, concave, and convex) were modeled to assess the influence of header shape on flame behavior. The results revealed distinct flow patterns, with the concave header promoting strong central flows and the convex header dispersing the flow outward. Temperature field analysis indicated that the

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19

Solmaz, Mehmet Burak, and Sitki Uslu. "Comparison of Reacting DDES and LES CFD Simulation Methodologies for a Dual Inlet Ramjet Engine Combustor." Isı Bilimi ve Tekniği Dergisi 45, no. 1 (2025): 10–21. https://doi.org/10.47480/isibted.1490666.

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The design of a dual inlet dump ramjet combustor is critical in the development of propulsion systems. Parameters such as pressure drop, pressure fluctuations, and combustion efficiency must be evaluated across various flight regimes. In this study, Large Eddy Simulation (LES) and Delayed Detached Eddy Simulation (DDES) techniques, coupled with the Steady Laminar Flamelet combustion model, are used to model a generic ramjet combustor. Grid convergence was ensured through the application of the Richardson extrapolation method, and the grid quality was evaluated using the M-index. A close agreem

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20

Kamarudin, Mohd Fathurrahman, Mohd Al-Hafiz Mohd Nawi, Azri Hariz Roslan, et al. "Investigating the Influence of Axial Velocity and Tangential Velocity on Combustion Characteristics in a Cylindrical Vortex Combustor." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 131, no. 2 (2025): 233–46. https://doi.org/10.37934/arfmts.131.2.233246.

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Efficient combustion is essential for various applications, including gas turbines, industrial furnaces, and propulsion systems. The interaction between axial and tangential velocities significantly influences combustion stability, flame shape, and pollutant formation. However, a comprehensive understanding of these effects in a cylindrical vortex combustor remains elusive. The primary of this study is to analyse how axial and tangential velocities impact combustion characteristics within the Cylindrical Vortex Combustor (CVC). Specifically, we aim to determine the optimal velocity combination

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21

Rimár, Miroslav, Ján Kizek, and Andrii Kulikov. "Numerical Modelling of Gaseous Fuel Combustion Process with the Stepwise Redistribution of Enriched Combustion Air." MATEC Web of Conferences 328 (2020): 02001. http://dx.doi.org/10.1051/matecconf/202032802001.

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The authors of this paper present the results of simulations for burner system design changes in the smelting aggregate. Based on the analysis of the existing burner system in the experimental aluminium smelting equipment, changes in the burner design were proposed. The obtained results are presented in tables and figures. The properties of the proposed changes were investigated using the simulation software ANSYS. The simulations confirmed the suitability of the proposed system for shortening the flame length and intensification of the mixing of gaseous media.

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22

Gonzalez-Juez, Esteban. "Numerical Simulations of Combustion Instabilities in a Combustor with an Augmentor-Like Geometry." Aerospace 6, no. 7 (2019): 82. http://dx.doi.org/10.3390/aerospace6070082.

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With the goal of assessing the capability of Computational Fluid Dynamics (CFD) to simulate combustion instabilities, the present work considers a premixed, bluff-body-stabilized combustor with well-defined inlet and outlet boundary conditions. The present simulations produce flow behaviors in good qualitative agreement with experimental observations. Notably, the flame flapping and standing acoustic waves seen in the experiments are reproduced by the simulations. Moreover, present predictions for the dominant instability frequency have an error of 7% and those of the rmspressure fluctuations

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23

Ahmed, E., and Y. Huang. "Flame volume prediction and validation for lean blow-out of gas turbine combustor." Aeronautical Journal 121, no. 1236 (2017): 237–62. http://dx.doi.org/10.1017/aer.2016.125.

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ABSTRACTLean Blow-Out (LBO) limits are critically important in the operation of aero engines. Previously, Lefebvre's LBO empirical correlation has been extended to the flame volume concept by the authors. Flame volume takes into account the effects of geometric configuration, spatial interaction of mixing jets, turbulence, heat transfer and combustion processes inside the gas turbine combustion chamber. For these reasons, LBO predictions based on flame volume are more accurate. Although LBO prediction accuracy has improved, it poses a challenge associated with Vfestimation in real gas turbine

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24

Tao, Feng, Sukhin Srinivas, Rolf D. Reitz, and David E. Foster. "Current status of soot modeling applied to diesel combustion simulations(Diesel Engines, Combustion Modeling I)." Proceedings of the International symposium on diagnostics and modeling of combustion in internal combustion engines 2004.6 (2004): 151–57. http://dx.doi.org/10.1299/jmsesdm.2004.6.151.

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25

Kang, Yiqin, Chenlu Wang, Gangyi Fang, Fei Xing, and Shining Chan. "Flow and Combustion Characteristics of Wave Rotor–Trapped Vortex Combustor System." Energies 16, no. 1 (2022): 326. http://dx.doi.org/10.3390/en16010326.

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Breaking through the limit of conventional compression and combustion, wave rotor and trapped vortex combustors are able to improve the thermal efficiency of gas turbines. Detailed two-dimensional numerical simulations based on Ansys Fluent were performed to study the flow and combustion characteristics of the wave rotor–trapped vortex combustor system. The calculated pressure characteristics agree with the experimental results giving a relative error for average pressure of 0.189% at Port 2 and of 0.672% at Port 4. The flow stratification characteristics and the periodic fluctuations were fou

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26

Guo, Kangkang, Yongjie Ren, Yiheng Tong, Wei Lin, and Wansheng Nie. "Analysis of self-excited transverse combustion instability in a rectangular model rocket combustor." Physics of Fluids 34, no. 4 (2022): 047104. http://dx.doi.org/10.1063/5.0086226.

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A methane/oxygen mixture is considered to be an appropriate propellant for many future rocket engines due to its practicality and low cost. To better understand the combustion instability in methane/oxygen-fed rocket engines, the spontaneous transverse combustion instability in a rectangular multi-element combustor (RMC) was analyzed both experimentally and numerically. Severe combustion instabilities occurred in the RMC during repeatable hot-fire tests. The physical mechanisms were systematically investigated through numerical simulations based on the stress-blended eddy simulation and flamel

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27

Nishiguchi, Hironobu, Masatoshi Kodera, and Sadatake Tomioka. "Effects of the Fuel Species on the Combustion Pressure in a Two Staged Fueled Scramjet Combustor." Aerospace 12, no. 1 (2025): 66. https://doi.org/10.3390/aerospace12010066.

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Two-staged fuel injection configuration for scramjet combustors has been shown to be effective in distributing heat release in the combustor for preventing the unstart transition of the engine by suppressing peak pressure while increasing the pressure thrust. In this study, the effect of fuel species on combustion characteristics in a two-staged fueled scramjet combustor was investigated. Wall pressure measurements in a two-staged fueled scramjet combustor were conducted in a combustion wind tunnel facility with fuels having different reactivity, such as H2 and CH4. Reynolds-Averaged Navier–St

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28

Lipatnikov, Andrei N. "Numerical Simulations of Turbulent Combustion." Fluids 5, no. 1 (2020): 22. http://dx.doi.org/10.3390/fluids5010022.

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Yuan, Yixiang, Qinghua Zeng, Jun Yao, Yongjun Zhang, Mengmeng Zhao, and Lu Zhao. "Improving Blowout Performance of the Conical Swirler Combustor by Employing Two Parts of Fuel at Low Operating Condition." Energies 14, no. 6 (2021): 1681. http://dx.doi.org/10.3390/en14061681.

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Aiming at the problem of the narrow combustion stability boundary, a conical swirler was designed and constructed based on the concept of fuel distribution. The blowout performance was studied at specified low operating conditions by a combination of experimental testing and numerical simulations. Research results indicate that the technique of the fuel distribution can enhance the combustion stability and widen the boundary of flameout within the range of testing conditions. The increase of the fuel distribution ratio improves the combustion stability but leads to an increase in NOx emission

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Krishnamoorthy, Gautham, and Caitlyn Wolf. "Assessing the Role of Particles in Radiative Heat Transfer during Oxy-Combustion of Coal and Biomass Blends." Journal of Combustion 2015 (2015): 1–15. http://dx.doi.org/10.1155/2015/793683.

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This study assesses the required fidelities in modeling particle radiative properties and particle size distributions (PSDs) of combusting particles in Computational Fluid Dynamics (CFD) investigations of radiative heat transfer during oxy-combustion of coal and biomass blends. Simulations of air and oxy-combustion of coal/biomass blends in a 0.5 MW combustion test facility were carried out and compared against recent measurements of incident radiative fluxes. The prediction variations to the combusting particle radiative properties, particle swelling during devolatilization, scattering phase

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Alhumairi, Mohammed, and Özgür Ertunç. "Active-grid turbulence effect on the topology and the flame location of a lean premixed combustion." Thermal Science 22, no. 6 Part A (2018): 2425–38. http://dx.doi.org/10.2298/tsci170503100a.

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Lean premixed combustion under the influence of active-grid turbulence was computationally investigated, and the results were compared with experimental data. The experiments were carried out to generate a premixed flame at a thermal load of 9 kW from a single jet flow combustor. Turbulent combustion models, such as the coherent flame model and turbulent flame speed closure model were implemented for the simulations performed under different turbulent flow conditions, which were specified by the Reynolds number based on Taylor?s microscale, the dissipation rate of turbulence, and turbulent kin

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32

Geigle, Klaus Peter, Wolfgang Meier, Manfred Aigner, et al. "Phase-Resolved Laser Diagnostic Measurements of a Downscaled, Fuel-Staged Gas Turbine Combustor at Elevated Pressure and Comparison to LES Predictions." Journal of Engineering for Gas Turbines and Power 129, no. 3 (2006): 680–87. http://dx.doi.org/10.1115/1.2718222.

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A technical gas turbine combustor has been studied in detail with optical diagnostics for validation of large-eddy simulations (LES). OH* chemiluminescence, OH laser-induced fluorescence (LIF) and particle image velocimetry (PIV) have been applied to stable and pulsating flames up to 8 bar. The combination of all results yielded good insight into the combustion process with this type of burner and forms a database that was used for the validation of complex numerical combustion simulations. LES, including radiation, convective cooling, and air cooling, were combined with a reduced chemical sch

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Wang, Xinyan, and Hua Zhao. "Modelling Study of Cycle-To-Cycle Variations (CCV) in Spark Ignition (SI)-Controlled Auto-Ignition (CAI) Hybrid Combustion Engine by Using Reynolds-Averaged Navier–Stokes (RANS) and Large Eddy Simulation (LES)." Energies 15, no. 12 (2022): 4478. http://dx.doi.org/10.3390/en15124478.

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The spark ignition (SI)-controlled auto-ignition (CAI) hybrid combustion is characterized by early flame propagation combustion and subsequent auto-ignition combustion. The application of combined SI–CAI hybrid combustion can be used to effectively extend the operating range of CAI combustion and achieve smooth transitions between SI and CAI combustion modes. However, SI–CAI hybrid combustion can produce significant cycle-to-cycle variations (CCV). In order to better understand the sources of CCV and minimize its occurrence, the large eddy simulation (LES) and Reynolds-averaged Navier–Stokes (

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Dinde, Prashant, A. Rajasekaran, and V. Babu. "3D numerical simulation of the supersonic combustion of H2." Aeronautical Journal 110, no. 1114 (2006): 773–82. http://dx.doi.org/10.1017/s0001924000001640.

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Results from numerical simulations of supersonic combustion of H2 are presented. The combustor has a single stage fuel injection parallel to the main flow from the base of a wedge. The simulations have been performed using FLUENT. Realisable k-ε model has been used for modelling turbulence and single step finite rate chemistry has been used for modelling the H2-Air kinetics. All the numerical solutions have been obtained on grids with average value for wall y+ less than 40. Numerically predicted profiles of static pressure, axial velocity, turbulent kinetic energy and static temperature for bo

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35

Ott, F., J. Losacker, N. Schmitz, and H. Pfeifer. "Numerical investigation of radiative transfer during oxyfuel combustion of hydrogen and hydrogen enriched natural gas in the container glass industry." Journal of Physics: Conference Series 2685, no. 1 (2024): 012032. http://dx.doi.org/10.1088/1742-6596/2685/1/012032.

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Abstract The substitution of natural gas with hydrogen is one way to eliminate direct CO2 emissions. However, oxyfuel combustion of hydrogen or hydrogen enriched natural gas leads to different exhaust gas properties due to a changed composition compared to conventional combustion. In combustion simulation, the emissivity of a gas mixture is usually approximated using a Weighted Sum of Gray Gases (WSGG) model. Most of the existing WSGG models have been validated for natural gas combustion with air or oxyfuel and are therefore not applicable to hydrogen-oxyfuel combustion. CFD simulations showed

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Pandey, Krishna Murari, and Sukanta Roga. "CFD Analysis of Hypersonic Combustion of H₂-Fueled Scramjet Combustor with Cavity Based Fuel Injector at Flight Mach 6." Applied Mechanics and Materials 656 (October 2014): 53–63. http://dx.doi.org/10.4028/www.scientific.net/amm.656.53.

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This paper presents a numerical analysis of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach 6 with cavity based injection. Fuel is injected at supersonic speed of Mach 2 through a cavity based injector. These numerical simulations are aimed to study the flow structure, supersonic mixing and combustion for cavity based injection. For the reacting cases, the shock wave pattern is modified which is due to the strong heat release during combustion process. The shock structure and combustion phenomenon are not only affected by the geometry but also by t

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Chow, P. H. P., H. C. Watson, and T. Wallis. "Combustion in a high-speed rotary valve spark-ignition engine." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 221, no. 8 (2007): 971–90. http://dx.doi.org/10.1243/09544070jauto407.

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The current paper describes a study of combustion in the Bishop rotary valve engine by means of computation simulations. The combustion model was developed for this research at speeds up to 18 000 r/min and the results from the simulation were compared with experimental data. Sensitivity studies were performed in order to investigate the parametric effects on the combustion simulation of the engine. The major finding of this study was that convection of the flame kernels occurs and has a strong influence on the performance of the engine. The results indicated some insights as to how the combus

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Srinivasarao, Muddada, and Vanteru Mahendra Reddy. "Effect of Thermodiffusion on Non Premixed Flame in MILD Regime Using a Modified Reacting Solver." Defence Science Journal 74, no. 2 (2024): 173–80. http://dx.doi.org/10.14429/dsj.74.19627.

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Numerical simulations for moderate and intense low oxygen dilution (MILD) combustion with essential solvers and detailed mechanisms involve more complications and computational time. Various advanced combustion modeling techniques have recently been developed to study MILD combustion characteristics. However, every combustion model has specific issues predicting the temperature and emissions of the MILD combustion flames. The diffusive nature of the MILD flame is considered, and individual Lewis numbers are investigated on a non-premixed flame. The current study analyzes the methane/hydrogen f

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Li, Jun, Meilin Zhu, Chang Geng, et al. "A Molecular Understanding of the Flame Retardant Mechanism of Zinc Stannate/Polypropylene Composites via ReaxFF Simulations." Inorganics 11, no. 6 (2023): 233. http://dx.doi.org/10.3390/inorganics11060233.

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As an important new flame retardant, zinc stannate (ZS) shows wide application prospects due to its many advantages. However, the flame retardant mechanism of composites made with polymer combined with ZS is still unclear. In particular, there is a lack of molecular level description of the micro-scale flame retardant mechanism. The combustion mechanism through molecular simulation technology has become an important research paradigm in the field of fire, which can provide new insights for the development of new materials. This work studied the flame retardant mechanism of composites consisten

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Meng, Nan, and Feng Li. "Large-eddy simulation of unstable non-reactive flow in a swirler combustor." Physics of Fluids 34, no. 11 (2022): 114107. http://dx.doi.org/10.1063/5.0122462.

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A comprehensive study on the influence of the unsteady non-reactive flow characteristics of turbulent flow in a three-stage swirl combustion chamber using power spectral density methods was conducted using large eddy simulations. The results demonstrated that instabilities were observed owing to large-scale vortex structures and periodic oscillations of the non-reactive flow. The boundary of the central recirculation zone (shear layers) enhanced the instability of the Helmholtz mode in the combustor. By considering the power spectral density of different monitoring points, the instability char

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Yousef, Wisam, Ziwan Li, Kai Zhou, and Jianping Yan. "A Novel Methodology for Calculating Combustion Characteristics Across the Combustion Zone Length." Energies 18, no. 6 (2025): 1470. https://doi.org/10.3390/en18061470.

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This paper introduces a novel mathematical model designed to determine combustion characteristics across the length of the combustion zone, underpinned by logical theoretical foundations and demonstrating notable alignment with experimental findings. The model facilitates the calculation of combustion efficiency based on inlet flow parameters (temperature, pressure, velocity, length, porosity, and air excess ratio), achieving efficiencies beyond conventional limits (η = 0.98–0.99) and reaching high values (η = 0.999–0.9999), which is crucial for optimizing low-emission combustors. Verification

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Hendricks, R. C., D. T. Shouse, W. M. Roquemore, et al. "Experimental and Computational Study of Trapped Vortex Combustor Sector Rig with High-Speed Diffuser Flow." International Journal of Rotating Machinery 7, no. 6 (2001): 375–85. http://dx.doi.org/10.1155/s1023621x0100032x.

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The Trapped Vortex Combustor (TVC) potentially offers numerous operational advantages over current production gas turbine engine combustors. These include lower weight, lower pollutant emissions, effective flame stabilization, high combustion efficiency, excellent high altitude relight capability, and operation in the lean burn or RQL modes of combustion. The present work describes the operational principles of the TVC, and extends diffuser velocities toward choked flow and provides system performance data. Performance data include EINOx results for various fuel-air ratios and combustor reside

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Di Sarli, Valeria, Marco Trofa, and Almerinda Di Benedetto. "A Novel Catalytic Micro-Combustor Inspired by the Nasal Geometry of Reindeer: CFD Modeling and Simulation." Catalysts 10, no. 6 (2020): 606. http://dx.doi.org/10.3390/catal10060606.

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A three-dimensional CFD model of a novel configuration of catalytic micro-combustor inspired by the nasal geometry of reindeer was developed using the commercial code ANSYS Fluent 19.0. The thermal behavior of this nature-inspired (NI) configuration was investigated through simulations of lean propane/air combustion performed at different values of residence time (i.e., inlet gas velocity) and (external convective) heat transfer coefficient. Simulations at the same conditions were also run for a standard parallel-channel (PC) configuration of equivalent dimensions. Numerical results show that

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Sui, Wenbo, and Carrie M. Hall. "Combustion phasing modeling and control for compression ignition engines with high dilution and boost levels." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 233, no. 7 (2018): 1834–50. http://dx.doi.org/10.1177/0954407018790176.

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Because fuel efficiency is significantly affected by the timing of combustion in internal combustion engines, accurate control of combustion phasing is critical. In this paper, a nonlinear combustion phasing model is introduced and calibrated, and both a feedforward model–based control strategy and an adaptive model–based control strategy are investigated for combustion phasing control. The combustion phasing model combines a knock integral model, burn duration model, and a Wiebe function to predict the combustion phasing of a diesel engine. This model is simplified to be more suitable for com

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Shibata, Gen, Kohei Yamamoto, Mikito Saito, Yuto Inoue, Yasumasa Amanuma, and Yoshimitsu Kobashi. "Optimization of combustion noise and thermal efficiency in diesel engines over a wide speed and load operational range." International Journal of Engine Research 21, no. 4 (2019): 698–712. http://dx.doi.org/10.1177/1468087419866069.

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Pre-mixed diesel combustion has the potential of offering high thermal efficiency with low emissions; however, this may result in loud combustion noise because of the high maximum rate of pressure rise. Combustion noise and thermal efficiency work in a trade-off relation, and it has not been possible to achieve high thermal efficiency with low combustion noise, so far. Our laboratory has worked on combustion noise simulations calculated from the heat release history, and it is now possible to calculate a heat release shape for high thermal efficiency with low combustion noise. In this article,

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Saputro, Herman, Heri Juwantono, Husin Bugis, et al. "Numerical simulation of flame stabilization in meso-scale vortex combustion." MATEC Web of Conferences 197 (2018): 08005. http://dx.doi.org/10.1051/matecconf/201819708005.

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A meso-scale vortex combustor has been designed in order to common flame quenching problems in meso/micro scale burning. Numerical simulations using Computational Fluid Dynamic (CFD) Ansys Release 19.0 Academic program was performed to determine a stable combustion flame. Combustor chamber made from two steps, first step diameter 6 mm with 4 mm depth, second step diameter size 8mm with 5 mm depth. This simulation used mixture of propane fuel-air. The fuel is fed through two channels of fuel inlet with 2 mm diameter. The variable of fuel flow rate was investigated in order to get the boundary o

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Jovanovic, Rastko, Krzysztof Strug, Bartosz Swiatkowski, Sławomir Kakietek, Krzysztof Jagiełło, and Dejan Cvetinovic. "Experimental and numerical investigation of flame characteristics during swirl burner operation under conventional and oxy-fuel conditions." Thermal Science 21, no. 3 (2017): 1463–77. http://dx.doi.org/10.2298/tsci161110325j.

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Oxy-fuel coal combustion, together with carbon capture and storage or utilization, is a set of technologies allowing to burn coal without emitting globe warming CO2. As it is expected that oxy-fuel combustion may be used for a retrofit of existing boilers, development of a novel oxy-burners is very important step. It is expected that these burners will be able to sustain stable flame in oxy-fuel conditions, but also, for start-up and emergency reasons, in conventional, air conditions. The most cost effective way of achieving dual-mode boilers is to introduce dual-mode burners. Numerical simula

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Stęchły, Katarzyna, Gabriel Wecel, and Derek B. Ingham. "CFD modelling of air and oxy-coal combustion." International Journal of Numerical Methods for Heat & Fluid Flow 24, no. 4 (2014): 825–44. http://dx.doi.org/10.1108/hff-02-2013-0066.

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Purpose – The main goal of this work was the CFD analysis of air and oxy-coal combustion, in order to develop a validated with experimental measurements model of the combustion chamber. Moreover, the purpose of this paper is to provide information about limitations of the sub-models implemented in commercial CFD code ANSYS Fluent version 13.0 for the oxy-coal combustion simulations. The influence of implementation of the weighted sum of gray gas model (WSGGM) with coefficients updated to oxy-coal combustion environment has been investigated. Design/methodology/approach – The sub-models validat

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Yu, Qiming, and Bhupendra Khandelwal. "Impact of Aromatic Hydrocarbons on Emissions in a Custom-Built High-Pressure Combustor." Energies 17, no. 16 (2024): 3939. http://dx.doi.org/10.3390/en17163939.

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This study addresses the ongoing demand for increased efficiency and reduced emissions in turbomachinery combustion systems. A custom-built high-pressure combustor was designed and manufactured at the Low Carbon Combustion Centre (LCCC) of the University of Sheffield to investigate the impact of different aromatic hydrocarbons on emission rates. The research involved the comprehensive testing of Jet−A1 fuel and six aromatic species blends under high-pressure conditions of 10 bar. Based on the numerical CFD simulations by ANSYS 19.2, tangential dual air injection and a strategically placed V-sh

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Jin, Xuan, Chibing Shen, Rui Zhou, and Xinxin Fang. "Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine." International Journal of Aerospace Engineering 2020 (September 15, 2020): 1–16. http://dx.doi.org/10.1155/2020/8867199.

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LOX/GCH4 pintle injector is suitable for variable-thrust liquid rocket engines. In order to provide a reference for the later design and experiments, three-dimensional numerical simulations with the Euler-Lagrange method were performed to study the effect of the initial particle diameter on the combustion characteristics of a LOX/GCH4 pintle rocket engine. Numerical results show that, as the momentum ratio between the radial LOX jet and the axial gas jet is 0.033, the angle between the LOX particle trace and the combustor axial is very small. Due to the large recirculation zones, premixed comb

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