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A special issue of Energies (ISSN 1996-1073).

Deadline for manuscript submissions: closed (31 October 2019) | Viewed by 16649

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Prof. Dr. In-Seuck Jeung

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Guest Editor

Aerospace Engineering, College of Engineering, Seoul National University, Seoul 08826, Korea
Interests: scramjet and ramjet combustion; shock induced combustion; detonation; hydrogen leak explosion; gas turbine combustors; ram accelerators; ramjet intake aerodynamics; laser propulsion; laser plasma flow control; aero-optic analysis; hypersonic aerothermodynamics; hypervelocity facility design; CubeSat development and operation

Special Issue Information

Dear Colleagues,

In recent decades, we have seen quite amazing progress in the development of scramjet engine combustors, tested both in facilities on the ground and in actual flight experiments during hypersonic speed. In parallel, hypersonic vehicles have also been demonstrated around the world. For atmospheric hypersonic, trans-atmospheric, and space flights, ramjet and scramjet engines will be an excellent choice for air-breathing propulsion during atmospheric flight. Hence, this Guest Editor is inviting submissions for a Special Issue of Energies on the subject area of “Scramjet and Ramjet Combustion”.

This Special Issue will focus on various topics of interest for publication, including, but not limited to: All aspects with respect to air intake and combustion interaction, all modes of supersonic combustion, turbulent mixing, ignition and flame stabilization, combustion instabilities, ram–scram transition, throttling transition, measurement and test, innovative novel measurement, numerical simulation, intake-combustor integration, airframe-engine integration, fuel technologies, thermal management, scramjet engine programs, and so on.

Prof. In-Seuck Jeung
Guest Editor

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Keywords

Ignition and flame stabilization
Supersonic turbulent mixing
Endothermic fuel
Ram–scram transition
Combustion instabilities
Dual-mode scramjet
Dual-combustion scramjet
Intake aerodynamics influence
Ground test facilities
Fight test
Numerical simulation

Published Papers (5 papers)

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Research

21 pages, 23645 KiB

Open AccessArticle

Combined Diagnostic Analysis of Dynamic Combustion Characteristics in a Scramjet Engine

by Seung-Min Jeong and Jeong-Yeol Choi

Energies 2020, 13(15), 4029; https://doi.org/10.3390/en13154029 - 04 Aug 2020

Cited by 9 | Viewed by 3057

Abstract

In this work, the dynamic combustion characteristics in a scramjet engine were investigated using three diagnostic data analysis methods: DMD (Dynamic Mode Decomposition), STFT (Short-Time Fourier Transform), and CEMA (Chemical Explosive Mode Analysis). The data for the analyses were obtained through a 2D numerical experiment using a DDES (Delayed Detached Eddy Simulation) turbulence model, the UCSD (University of California at San Diego) hydrogen/oxygen chemical reaction mechanism, and high-resolution schemes. The STFT was able to detect that oscillations above 50 kHz identified as dominant in FFT results were not the dominant frequencies in a channel-type combustor. In the analysis using DMD, it was confirmed that the critical point that induced a complete change of mixing characteristics existed between an injection pressure of 0.75 MPa and 1.0 MPa. A combined diagnostic analysis that included a CEMA was performed to investigate the dynamic combustion characteristics. The differences in the reaction steps forming the flame structure under each combustor condition were identified, and, through this, it was confirmed that the pressure distribution upstream of the combustor dominated the dynamic combustion characteristics of this scramjet engine. From these processes, it was confirmed that the combined analysis method used in this paper is an effective approach to diagnose the combustion characteristics of a supersonic combustor. Full article

(This article belongs to the Special Issue Scramjet and Ramjet Combustion)

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17 pages, 6059 KiB

Open AccessArticle

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

by Seoeum Han, Sangyoon Lee and Bok Jik Lee

Energies 2020, 13(3), 606; https://doi.org/10.3390/en13030606 - 31 Jan 2020

Cited by 6 | Viewed by 3353

Abstract

This numerical study was conducted to investigate the flow properties in a model scramjet configuration of the experiment in the T4 shock tunnel. In most numerical simulations of flows in shock tunnels, the inflow conditions in the test section are determined by assuming the thermal equilibrium of the gas. To define the inflow conditions in the test section, the numerical simulation of the nozzle flow with the given nozzle reservoir conditions from the experiment is conducted by a thermochemical nonequilibrium computational fluid dynamics (CFD) solver. Both two-dimensional (2D) and three-dimensional (3D) numerical simulations of the flow in a model scramjet were conducted without fuel injection. Simulations were performed for two types of inflow conditions: one for thermochemical nonequilibrium states obtained from the present nozzle simulation and the other for the data available using the thermal equilibrium and chemical nonequilibrium assumptions. The four results demonstrate the significance of the modelling approach for choosing between 2D or 3D, and thermal equilibrium or nonequilibrium. Full article

(This article belongs to the Special Issue Scramjet and Ramjet Combustion)

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16 pages, 3681 KiB

Open AccessArticle

The Effect of Fuel Injection Location on Supersonic Hydrogen Combustion in a Cavity-Based Model Scramjet Combustor

by Eunju Jeong, Sean O’Byrne, In-Seuck Jeung and A. F. P. Houwing

Energies 2020, 13(1), 193; https://doi.org/10.3390/en13010193 - 01 Jan 2020

Cited by 16 | Viewed by 3853

Abstract

Supersonic combustion experiments were performed using three different hydrogen fuel-injection configurations in a cavity-based model scramjet combustor with various global fuel–air equivalence ratios. The configurations tested were angled injection at 15° to the flow direction upstream of the cavity, parallel injection from the front step, and upstream injection from the rear ramp. Planar laser-induced fluorescence of the hydroxyl radical and time-resolved pressure measurements were used to investigate the flow characteristics. Angled injection generated a weak bow shock in front of the injector and recirculation zone to maintain the combustion as the equivalence ratio increased. Parallel and upstream injections both showed similar flame structure over the cavity at low equivalence ratio. Upstream injection enhanced the fuel diffusion and enabled ignition with a shorter delay length than with parallel injection. The presence of a flame near the cavity was determined while varying the fuel injection location, the equivalence ratio, and total enthalpy of the air flow. The flame characteristics agreed with the correlation plot for the stable flame limit of non-premixed conditions. The pressure increase in the cavity for reacting flow compared to non-reacting flow was almost identical for all three configurations. More than 300 mm downstream of the duct entrance, averaged pressure ratios at low global equivalence ratio were similar for all three injection configurations. Full article

(This article belongs to the Special Issue Scramjet and Ramjet Combustion)

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12 pages, 1366 KiB

Open AccessArticle

Modeling of Scramjet Combustors Based on Model Migration and Process Similarity

by Tao Cui and Yang Ou

Energies 2019, 12(13), 2516; https://doi.org/10.3390/en12132516 - 30 Jun 2019

Cited by 6 | Viewed by 2261

Abstract

Contributed by the low cost, the simulation method is considered an attractive option for the optimization and design of the supersonic combustor. Unfortunately, accurate and satisfactory modeling is time-consuming and cost-consuming because of the complex processes and various working conditions. To address this issue, a mathematical modeling for the combustor on the basis of the clustering algorithm, machine learning algorithm, and model migration strategy is developed in this paper. A general framework for the migration strategy of the combustor model is proposed among the similar combustors, and the base model, which is developed by training the machine learning model with data from the existing combustion processes, is amended to fit the unexampled combustor using the model migration strategy with a few data. The simulation results validate the effectiveness of the development strategy, and the migrated model is proved to be suitable for the new combustor in higher accuracy with less time and calculation. Full article

(This article belongs to the Special Issue Scramjet and Ramjet Combustion)

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13 pages, 6015 KiB

Open AccessFeature PaperArticle

Forced Combustion Characteristics Related to Different Injection Locations in Unheated Supersonic Flow

by Chae-Hyoung Kim and In-Seuck Jeung

Energies 2019, 12(9), 1746; https://doi.org/10.3390/en12091746 - 08 May 2019

Cited by 6 | Viewed by 2598

Abstract

This work focuses on forced combustion with regards to the relationship between vent mixer models and several injection locations in unheated supersonic flow. A plasma jet torch was used to ignite the hydrogen-air mixture in a laboratory-scaled combustor duct. The flow field of the combustion was visualized with pressure and gas-sampling measurements. The vent mixers indicate good dispersion characteristics of the mixture for both parallel and normal 1 injections. However, forced combustion is dominantly governed by the injection rate toward the plasma jet (hot source) because the combustible region is restricted under the cold main flow. For this reason, the parallel injection, which provides the hydrogen-air mixture directly toward the plasma jet, shows good combustion performance. The normal 1 injection interacted with the vent mixers and shows slightly good combustion performance. Lastly, the normal 2 injection is little affected by the vent mixers and has poor combustion performance. Full article

(This article belongs to the Special Issue Scramjet and Ramjet Combustion)

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