Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
3.0
2.6
Journals
Aerospace
Special Issues
Large-Eddy Simulation Applications of Combustion Systems
share announcement

Large-Eddy Simulation Applications of Combustion Systems

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 October 2022) | Viewed by 8605

Special Issue Editor

Dr. Eugenio Giacomazzi

E-Mail Website
Guest Editor
ENEA/Laboratory of Processes and Systems Engineering for Energy Decarbonisation (IPSE), Division of Production, Storage and Use of Energy (PSU), Department of Energy Technologies and Renewable Sources (TERIN), TERIN-PSU-IPSE, S.P. 081, Via Anguillarese, 301, Santa Maria di Galeria, 00123 Rome, Italy
Interests: CFD simulation; numerical simulation; signal processing; computational fluid dynamics; fluid mechanics; numerical modeling; thermal engineering; engineering thermodynamics; numerical analysis; modeling and simulation

Special Issue Information

Dear Colleagues,

Since its very beginning, the aerospace sector has consistently promoted scientific research. In particular, combustion systems, which encompass most aerospace engines for thrust generation, have been driving investigations into thermofluid dynamics, with a positive impact on other sectors, too, such as power generation for electric systems. The great interest in burning green propellants in gas turbines has opened new challenges for the identification of the most suitable combustion technology. The renewed interest in access to space adopting reusable launchers is pushing research in liquid and air-breathing rocket engines. Further, chemical propulsion has a main role in hypersonic and supersonic vehicles for atmospheric and trans-atmospheric flights and in missile interception. In such applications, the dynamics of reacting flows plays a central role. Although not yet fully integrated in the design process at industrial level due to its longer time-to-solution with respect to the commonly adopted RANS/FANS approach, large eddy simulation, able to capture large (resolved) turbulent scales behavior, is of great help in investigating dynamic physical mechanisms and in looking for control strategies to develop innovative combustion systems.

This Special Issue of Aerospace focuses on articles dealing with LES numerical investigation of combustion systems for gas turbines, ramjet, scramjet, liquid, solid, and hybrid rocket engines, especially covering topics where the role of dynamics is crucial, such as thermoacoustic instabilities, flame stabilization, blow-off, and real gas effects.

Dr. Eugenio Giacomazzi
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • combustion
  • thermo-acoustics
  • flame stabilization
  • flame blow-off
  • mixing
  • real gas
  • high-pressure
  • trans-critical injection
  • supercritical flow
  • radiative energy transfer
  • gas turbine
  • ramjet
  • scramjet
  • rocket

Published Papers (4 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

24 pages, 10465 KiB  
Article
Numerical Simulations of Spray Combustion in Jet Engines
by Arvid Åkerblom, Francesco Pignatelli and Christer Fureby
Aerospace 2022, 9(12), 838; https://doi.org/10.3390/aerospace9120838 - 16 Dec 2022
Cited by 3 | Viewed by 2527
Abstract
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 [...] Read more.
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 characteristics. In this study, we examine premixed and pre-vaporized combustion of dodecane, Jet A, and a synthetic test fuel, C1, based on the alcohol-to-jet (ATJ) certified pathway behind an equilateral bluff-body flameholder, spray combustion of Jet A and C1 in a laboratory combustor, and spray combustion of Jet A and C1 in a single-sector model of a helicopter engine by means of numerical simulations. A finite rate chemistry (FRC) large eddy simulation (LES) approach is adopted and used together with small comprehensive reaction mechanisms of around 300 reversible reactions. Comparison with experimental data is performed for the bluff-body flameholder and laboratory combustor configurations. Good agreement is generally observed, and small to marginal differences in combustion behavior are observed between the different fuels. Full article
(This article belongs to the Special Issue Large-Eddy Simulation Applications of Combustion Systems)
►▼ Show Figures

Figure 1

22 pages, 9532 KiB  
Article
Large Eddy Simulation of Combustion for High-Speed Airbreathing Engines
by Christer Fureby, Guillaume Sahut, Alessandro Ercole and Thommie Nilsson
Aerospace 2022, 9(12), 785; https://doi.org/10.3390/aerospace9120785 - 01 Dec 2022
Cited by 6 | Viewed by 1975
Abstract
Large Eddy Simulation (LES) has rapidly developed into a powerful computational methodology for fluid dynamic studies, between Reynolds-Averaged Navier–Stokes (RANS) and Direct Numerical Simulation (DNS) in both accuracy and cost. High-speed combustion applications, such as ramjets, scramjets, dual-mode ramjets, and rotating detonation engines, [...] Read more.
Large Eddy Simulation (LES) has rapidly developed into a powerful computational methodology for fluid dynamic studies, between Reynolds-Averaged Navier–Stokes (RANS) and Direct Numerical Simulation (DNS) in both accuracy and cost. High-speed combustion applications, such as ramjets, scramjets, dual-mode ramjets, and rotating detonation engines, are promising propulsion systems, but also challenging to analyze and develop. In this paper, the building blocks needed to perform LES of high-speed combustion are reviewed. Modelling of the unresolved, subgrid terms in the filtered LES equations is highlighted. The main families of combustion models are presented, focusing on finite-rate chemistry models. The density-based finite volume method and the reaction mechanisms commonly employed in LES of high-speed H2-air combustion are briefly reviewed. Three high-speed combustor applications are presented: an experiment of supersonic flame stabilization behind a bluff body, a direct connect facility experiment as a transition case from ramjet to scramjet operation mode, and the STRATOFLY MR3 Small-Scale Flight Experiment. Several combinations of turbulence and combustion models are compared. Comparisons with experiments are also provided when available. Overall, the results show good agreement with experimental data (e.g., shock train, mixing, wall heat flux, transition from ramjet to scramjet operation mode). Full article
(This article belongs to the Special Issue Large-Eddy Simulation Applications of Combustion Systems)
►▼ Show Figures

Figure 1

19 pages, 4689 KiB  
Article
Large Eddy Simulation of the Influences of the Pilot-Stage Structure on the Flow Characteristics in a Centrally Staged High-Temperature-Rise Combustor
by Ge Hu, Qiongyao Qin, Wu Jin and Jianzhong Li
Aerospace 2022, 9(12), 782; https://doi.org/10.3390/aerospace9120782 - 01 Dec 2022
Cited by 3 | Viewed by 1594
Abstract
Centrally staged combustion technique is often used in the military high-temperature-rise combustor. The pilot-stage structure affects the flow characteristics in the centrally staged combustor, which further affects the performance of ignition, combustion, and emission of military aero-engines. In order to increase the flow [...] Read more.
Centrally staged combustion technique is often used in the military high-temperature-rise combustor. The pilot-stage structure affects the flow characteristics in the centrally staged combustor, which further affects the performance of ignition, combustion, and emission of military aero-engines. In order to increase the flow capacity of the swirler, the swirler with a non-rotating channel structure was designed. In this work, the influences of the pilot-stage structure on the flow characteristics in the centrally staged high-temperature-rise combustor are investigated. The flow fields of combustors with different pilot-stage swirl numbers (0.44, 0.60, and 0.71) are analyzed by large eddy simulation (LES). The results demonstrate that the primary recirculation zone (PRZ) becomes gradually longer and wider as the pilot-stage swirl number increases. In the combustors with three different pilot-stage structures, the precessing vortex core (PVC) was formed near the shear layer at the outlet of the pilot stage. The PVC frequency decreased from 1670 Hz to 1425 Hz and 1400 Hz with the increase of the pilot-stage swirl number from 0.44 to 0.60 and 0.71, respectively, and the breakdown position of the PVC shifted forward. The proper orthogonal decomposition (POD) and dynamic mode decomposition (DMD) methods are used to analyze the dynamic flow fields. It was observed that the corresponding frequency of the main pulsation structure decreased, and the flow instability was aggravated with the increase of the pilot-stage swirl number. The results deepen the understanding of the influences of the pilot-stage structure on the flow characteristics in the centrally staged high-temperature-rise combustor. Full article
(This article belongs to the Special Issue Large-Eddy Simulation Applications of Combustion Systems)
►▼ Show Figures

Figure 1

23 pages, 9463 KiB  
Article
Flame Anchoring of an H2/O2 Non-Premixed Flamewith O2 Transcritical Injection
by Eugenio Giacomazzi, Donato Cecere and Nunzio Arcidiacono
Aerospace 2022, 9(11), 707; https://doi.org/10.3390/aerospace9110707 - 11 Nov 2022
Viewed by 1467
Abstract
The article is devoted to the analysis of the flame anchoring mechanism in the test case MASCOTTE C-60 RCM2 on supercritical hydrogen/oxygen combustion at 60 bar, with transcritical (liquid) injection of oxygen. The case is simulated by means of the in-house parallel code [...] Read more.
The article is devoted to the analysis of the flame anchoring mechanism in the test case MASCOTTE C-60 RCM2 on supercritical hydrogen/oxygen combustion at 60 bar, with transcritical (liquid) injection of oxygen. The case is simulated by means of the in-house parallel code HeaRT in the three-dimensional LES framework. The cubic Peng–Robinson equation of state in its improved translated volume formulation is assumed. Diffusive mechanisms and transport properties are accurately modeled. A finite-rate detailed scheme involving the main radicals, already validated for high-pressure H2/O2 combustion, is adopted. The flow is analysed in terms of temperature, hydrogen and oxygen instantaneous spatial distributions, evidencing the effects of the vortex shedding from the edges of the hydrogen injector and of the separation of the oxygen stream in the divergent section of its tapered injector on the flame anchoring and topology. Combustion conditions are characterised by looking at the equivalence ratio and compressibility factor distributions. Full article
(This article belongs to the Special Issue Large-Eddy Simulation Applications of Combustion Systems)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-4
Back to TopTop