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Numerical Simulation of Turbulent Combustion

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "A: Sustainable Energy".

Deadline for manuscript submissions: closed (31 December 2021) | Viewed by 5773

Special Issue Editor


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Guest Editor
Department of Aerospace Engineering, Seoul National University, Seoul 08826, Korea
Interests: CFD; combustion; propulsion; flame; detonation

Special Issue Information

Dear Colleagues,

With the recent advances in computational fluid dynamics, turbulence modeling, and computing power, numerical simulations of turbulent combustion involved in most practical applications utilizing energy conversion via combustion have been becoming a tangible task. The need for numerical simulations is ever increasing in various sectors of combustion applications such as IC engines, gas turbines for power generation and aviation, ramjet/scramjet propulsion systems, explosion and safety, and so on. In those applications, the primary goals of research and development are to improve energy conversion efficiency, to reduce emissions, and to avoid combustion instability. While the fidelity of numerical solutions for turbulent combustion is a crucial factor in such efforts, ascertaining the fidelity of any numerical simulations is still a very challenging task for researchers. There have been tremendous efforts in developing novel turbulent combustion modeling approaches seeking an optimal tradeoff between modeling accuracy and computational costs. As a result, researchers now have a wide variety of options, for example, between RANS, LES, and their hybrid, and among flamelet-based methods, conditional moment closure, and the transported PDF method, just to name a few. However, we still lack experience and data to come up with the best practices of numerical simulations in any applications.

This Special Issue is open to research and review articles of numerical simulations of turbulent combustion, focused on the practical applications and validation of any turbulent combustion modeling, in order to collect contemporary usages of computational fluid dynamics in the field of combustion science and engineering hoping to share between us insights on what the accomplishments, limits, costs, and room to further develop are in the field of turbulent combustion modeling and applications. In this sense, not only successful simulations but also failure stories are welcome to be communicated in this Special Issue.

Prof. Dr. Bok Jik Lee
Guest Editor

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Keywords

  • validation against canonical turbulent flames
  • validation against measurements
  • turbulent flames at near-limit conditions
  • combustion instability of turbulent flames
  • interaction of turbulence and combustion
  • turbulent combustion at elevated pressures
  • application to IC engines, gas turbines, rocket propulsion, ramjet/scramjets
  • deflagration and detonation
  • assessment of turbulent combustion models
  • application of machine-learning and data-driven approaches for turbulent combustion

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Published Papers (2 papers)

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24 pages, 8338 KiB  
Article
Effect of the Preheated Oxidizer Temperature on Soot Formation and Flame Structure in Turbulent Methane-Air Diffusion Flames at 1 and 3 atm: A CFD Investigation
by Subrat Garnayak, Subhankar Mohapatra, Sukanta K. Dash, Bok Jik Lee and V. Mahendra Reddy
Energies 2021, 14(12), 3671; https://doi.org/10.3390/en14123671 - 20 Jun 2021
Cited by 3 | Viewed by 2628
Abstract
This article presents the results of computations on pilot-based turbulent methane/air co-flow diffusion flames under the influence of the preheated oxidizer temperature ranging from 293 to 723 K at two operating pressures of 1 and 3 atm. The focus is on investigating the [...] Read more.
This article presents the results of computations on pilot-based turbulent methane/air co-flow diffusion flames under the influence of the preheated oxidizer temperature ranging from 293 to 723 K at two operating pressures of 1 and 3 atm. The focus is on investigating the soot formation and flame structure under the influence of both the preheated air and combustor pressure. The computations were conducted in a 2D axisymmetric computational domain by solving the Favre averaged governing equation using the finite volume-based CFD code Ansys Fluent 19.2. A steady laminar flamelet model in combination with GRI Mech 3.0 was considered for combustion modeling. A semi-empirical acetylene-based soot model proposed by Brookes and Moss was adopted to predict soot. A careful validation was initially carried out with the measurements by Brookes and Moss at 1 and 3 atm with the temperature of both fuel and air at 290 K before carrying out further simulation using preheated air. The results by the present computation demonstrated that the flame peak temperature increased with air temperature for both 1 and 3 atm, while it reduced with pressure elevation. The OH mole fraction, signifying reaction rate, increased with a rise in the oxidizer temperature at the two operating pressures of 1 and 3 atm. However, a reduced value of OH mole fraction was observed at 3 atm when compared with 1 atm. The soot volume fraction increased with air temperature as well as pressure. The reaction rate by soot surface growth, soot mass-nucleation, and soot-oxidation rate increased with an increase in both air temperature and pressure. Finally, the fuel consumption rate showed a decreasing trend with air temperature and an increasing trend with pressure elevation. Full article
(This article belongs to the Special Issue Numerical Simulation of Turbulent Combustion)
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22 pages, 8086 KiB  
Article
Numerical Simulation of a GH2/LOx Single Injector Combustor and the Effect of the Turbulent Schmidt Number
by Won-Sub Hwang, Woojoo Han, Kang Y. Huh, Juhoon Kim, Bok Jik Lee and Jeong-Yeol Choi
Energies 2020, 13(24), 6616; https://doi.org/10.3390/en13246616 - 15 Dec 2020
Cited by 4 | Viewed by 2527
Abstract
A large-eddy simulation (LES) of a gaseous hydrogen/liquid oxygen (GH2/LOX) single-injector rocket combustor is performed in this study. The Redlich–Kwong–Peng–Robinson (RK–PR) equation of state is used to simulate the real-gas effect under high-pressure conditions, and the steady laminar flamelet [...] Read more.
A large-eddy simulation (LES) of a gaseous hydrogen/liquid oxygen (GH2/LOX) single-injector rocket combustor is performed in this study. The Redlich–Kwong–Peng–Robinson (RK–PR) equation of state is used to simulate the real-gas effect under high-pressure conditions, and the steady laminar flamelet model (SLFM) is implemented to simulate fast chemistry, such as a H2/O2 reaction. From the numerical simulation, the characteristics of time-averaged flow and flame fields are obtained, and their relationship with the real-gas effect is investigated. It is possible to investigate unsteady flame features and the mixing mechanism of propellants in detail by examining multiple snapshots of the field contour. Another purpose of the study is to investigate the differences in flow and flame structures according to the variation in the turbulent Schmidt number. By comparing the simulation result with the natural OH* emission image and temperature profiles from experimental data, the appropriate range of the turbulent Schmidt number for the simulation is obtained. Furthermore, this paper suggests the usefulness and validity of the current research by quantitatively comparing (i.e., temperature profiles) numerical results with those of existing literature. Full article
(This article belongs to the Special Issue Numerical Simulation of Turbulent Combustion)
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