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Special Issue "Fundamental Detonation Mechanism and Advanced Detonation Propulsion Technology"

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A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: 31 August 2023 | Viewed by 5862

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Prof. Dr. Bo Zhang

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Guest Editor

School of Aeronautics and Astronautics, Shanghai Jiaotong University, Shanghai 200240, China
Interests: dynamics of gaseous detonation; shock waves; explosion characteristics of combustible mixtures; lean blow-out in turbine combustors

Prof. Dr. Honghui Teng

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Guest Editor

School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
Interests: dynamics of detonation

Prof. Dr. Jeong Yeol Choi

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Guest Editor

Department of Aerospace Engineering, Pusan National University, Busan 46241, Republic of Korea
Interests: propulsion and combustion phenonmena in rocket, scramjet, and detonation engines; detonation; supersonic combustion; turbulent combustion; supercritical combustion; high-resolution numerical methods; high-performance computing; combustion experiments; visualization of high-speed flows
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Special Issue Information

Dear Colleagues,

In recent years, there has been increasing interest in developing detonation-based engines, such as Pulsed (PDEs), Rotating (RDEs) and Oblique Detonation Engines (ODEs), for aeronautics and astronautics propulsion applications due to the high propulsion performance afforded by detonation. However, challenges remain in the application of detonation engines; thus, the fundamental detonation phenomena (e.g., initiation, propagation limits and failure) and their mechanisms must be better understood prior to the application of detonation in advanced propulsion technology.

For this Special Issue, we invite authors to contribute high-quality original papers covering fundamental detonation phenomena and their physics, and new developments in technology associated with the application of detonation, especially for PDEs, RDEs and ODEs. We also welcome papers discussing new theoretical, analytical, experimental and numerical developments.

Prof. Dr. Bo Zhang
Prof. Dr. Honghui Teng
Prof. Dr. Jeong Yeol Choi
Guest Editors

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 1800 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

detonation
shock waves
initiation
propagation limits
detonation failure
Pulsed Detonation Engines
Rotating Detonation Engines
Oblique Detonation Engines

Published Papers (6 papers)

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Research

Open AccessArticle

Criticality for Oblique Detonation Waves Induced by a Finite Wedge in a Hydrogen–Air Mixture

Jianxiu Qin

and

Dehua Zhu

Aerospace 2023, 10(6), 508; https://doi.org/10.3390/aerospace10060508 - 27 May 2023

Viewed by 350

Abstract

Two-dimensional oblique detonation waves (ODWs) induced by finite wedges in a stoichiometric hydrogen–air mixture have been investigated numerically based on reactive Euler equations with a detailed chemical reaction model. The main zone affected by the expansion wave emanating from the turning point of a wedge is the flowfield downstream of the intersection point of the oblique shock wave (OSW) and the expansion wave. The ODW would be reduced to Chapman–Jouguet (CJ) detonation or decoupled combustion downstream. Three combustion regimes, detonation, decoupled combustion, and no ignition, were observed successively, as the wedge length decreases. It is found that the location of the intersection point is a key parameter for the detonation initiation. When the intersection point is located upstream of the ODW transition point, the expansion wave may quench ODW. Then, the critical wedge length is obtained by theoretical analysis of wave structures and the initiation criterion of ODWs for finite wedges is proposed. When the wedge length is greater than the critical wedge length, ODWs can be initiated. On the contrary, the initiation of ODWs do not occur. For wedge lengths small enough, no ignition occurs. Previously proposed criteria that use the induction length are also examined and compared with the present critical wedge length criterion in this study, and the latter is proven to achieve better results. Full article

(This article belongs to the Special Issue Fundamental Detonation Mechanism and Advanced Detonation Propulsion Technology)

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Open AccessArticle

Effects of Ozone Addition on Multi-Wave Modes of Hydrogen–Air Rotating Detonations

Yang Wang

Cheng Tian

and

Pengfei Yang

Aerospace 2023, 10(5), 443; https://doi.org/10.3390/aerospace10050443 - 11 May 2023

Viewed by 587

Abstract

Ozone addition presents a promising approach for optimizing and regulating both combustion and ignition mechanisms. In Rotating Detonation Engines (RDEs), investigating the impact of ozone addition is particularly important due to the fact of their unique operating conditions and potential for improved efficiency. This study explores the influence of ozone concentration, total temperature, and equivalent ratio on the combustion characteristics of a hydrogen–air mixture infused with ozone. Utilizing the mixture as a propellant, the combustion chamber of a continuous rotating detonation engine is replicated through an array of injection ports, with numerical simulations conducted to analyze the detonation wave combustion mode. Our results show that an increase in total temperature leads to an increase in the number of detonation waves. Incorporating a minor quantity of ozone can facilitate the ignition process for the detonation wave. Increasing the ozone content can result in the conversion from a single-wave to dual-wave or multi-wave mode, providing a more stable combustion interface. A low ozone concentration acts as an auxiliary ignition agent and can significantly shorten the induction time. As the total temperature increases, the detonation propagation velocity and the peak heat release rate both decrease concurrently, which leads to a decline in the exit total pressure and an augmentation in the specific impulse. Employing ozone exerts a minimal impact on the detonation propagation and the overall propulsion performance. The requirement for ozone-assisted initiation differs noticeably between rich and lean combustion. Full article

(This article belongs to the Special Issue Fundamental Detonation Mechanism and Advanced Detonation Propulsion Technology)

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Open AccessArticle

Unsteady Oblique Detonation Waves in a Tunnel Induced by Inflow Mach Number Variation

and

Aerospace 2023, 10(4), 330; https://doi.org/10.3390/aerospace10040330 - 27 Mar 2023

Viewed by 720

Abstract

Oblique detonation waves (ODWs) have been investigated widely aiming at facilitating their application in hypersonic engines. However, there is a lack of research on unsteady ODWs which are unavoidable in the hypersonic air-breathing scenario. In this study, unsteady ODWs triggered by the variation of the inflow Mach number (M₀) have been studied and the geometric model is a tunnel with an outward-deflection upper wall to mimic an engine outlet. Numerical results demonstrate that when M₀ deviates from the designed state, two typical wave structures arise, featuring a Mach stem of detonation or a post-corner recirculation zone. A sudden change in M₀ leads to the transition of these two structures, generating unsteady ODWs temporally with a multi-segment-complex wave surface caused by triple points. The wave structures near the corner have been analyzed in detail, revealing how the Mach stem and the recirculation zone evolve into each other. Furthermore, the effects of unsteady ODWs on hypersonic propulsion applications have been discussed, providing possible ways to suppress the Mach stem of detonation. Full article

(This article belongs to the Special Issue Fundamental Detonation Mechanism and Advanced Detonation Propulsion Technology)

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Open AccessArticle

Numerical Investigation of the Detonation Cell Bifurcation with Decomposition Technique

Pradeep Kumar Pavalavanni

Jae-Eun Kim

Min-Seon Jo

and

Jeong-Yeol Choi

Aerospace 2023, 10(3), 318; https://doi.org/10.3390/aerospace10030318 - 22 Mar 2023

Viewed by 643

Abstract

Bifurcation of the characteristic cells into multiple smaller cells and decay of those cells into single large characteristic cell is observed frequently. In the present study the bifurcation phenomenon of the detonation front is investigated for marginally unstable detonations using decomposition technique. Numerical analysis is carried out with detailed chemical kinetics for detonation propagation in H₂/O₂ mixtures at 10 kPa. The dynamic characteristics of the instability at the detonation front, such as the local oscillation frequency and the coherent spatial structure of the oscillation are also studied with dynamic mode decomposition (DMD) technique. The coherent structures of the primary and secondary detonation cells are analyzed during the cell bifurcation process and the mechanism in which the secondary cells are formed is investigated. It is demonstrated that the modal analysis categorizes the instability phenomena clearly and can be effectively utilized to identify the origin and source of the instability. Full article

(This article belongs to the Special Issue Fundamental Detonation Mechanism and Advanced Detonation Propulsion Technology)

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Open AccessArticle

Numerical Study of Unstable Shock-Induced Combustion with Different Chemical Kinetics and Investigation of the Instability Using Modal Decomposition Technique

Pradeep Kumar Pavalavanni

Min-Seon Jo

Jae-Eun Kim

and

Jeong-Yeol Choi

Aerospace 2023, 10(3), 292; https://doi.org/10.3390/aerospace10030292 - 15 Mar 2023

Cited by 1 | Viewed by 661

Abstract

An unstable shock-induced combustion (SIC) case around a hemispherical projectile has been numerically studied which experimentally produced a regular oscillation. Comparison of detailed H₂/O₂ reaction mechanisms is made for the numerical simulation of SIC with higher-order numerical schemes intended for the use of the code for the hypersonic propulsion and supersonic combustion applications. The simulations show that specific reaction mechanisms are grid-sensitive and produce spurious reactions in the high-temperature region, which trigger artificial instability in the oscillating flow field. The simulations also show that specific reaction mechanisms develop such spurious oscillations only at very fine grid resolutions. The instability mechanism is investigated using the dynamic mode decomposition (DMD) technique and the spatial structure of the decomposed modes are further analyzed. It is found that the instability triggered by the high-temperature reactions strengthens the reflecting compression wave and pushes the shock wave further and disrupts the regularly oscillating mechanism. The spatial coherent structure from the DMD analysis shows the effect of this instability in different regions in the regularly oscillating flow field. Full article

(This article belongs to the Special Issue Fundamental Detonation Mechanism and Advanced Detonation Propulsion Technology)

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Open AccessArticle

Experimental Proof of Concept of a Noncircular Rotating Detonation Engine (RDE) for Propulsion Applications

and

Aerospace 2023, 10(1), 27; https://doi.org/10.3390/aerospace10010027 - 28 Dec 2022

Viewed by 1258

Abstract

A noncircular engine cross-section could provide great flexibility in the integration of propulsion into the airframe. In this work, a tri-arc RDE was constructed and tested as an example of noncircular cross-sectioned RDE. The operational characteristics of detonation wave propagation and thrust performance were investigated and compared with an equivalent circular RDE under the same operating conditions. High-speed camera images, short-time Fourier transform (STFT), and fast Fourier transform (FFT) were used for the investigation. The tri-arc RDE showed very similar characteristics to the circular RDE but exhibited slightly better stability and propulsion performance than the circular RDE. We consider that repeated curvature changes positively affect the stability of detonation wave propagation. The experimental data show contradicting results from the numerical analysis with a homogeneous mixture assumption in which the detonation pressures at the convex corner were greater than those at the concave corner. It is reasoned that the tri-arc injector design provides a non-uniform mixture composition, resulting in a strong detonation at the convex corner. Overall, the noncircular RDE of a tri-arc shaped cross-section is demonstrated, one which performs slightly better than an ordinary circular-shaped RDE both in detonation stability and performance. Full article

(This article belongs to the Special Issue Fundamental Detonation Mechanism and Advanced Detonation Propulsion Technology)

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