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Aerospace
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Advances in Detonative Propulsion
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Advances in Detonative Propulsion

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

Deadline for manuscript submissions: 15 July 2024 | Viewed by 4884

Special Issue Editors

Dr. Yunfeng Liu

E-Mail Website
Guest Editor
Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
Interests: oblique detonation engine; detonative propulsion; supersonic combustion; scramjets; high-enthalpy shock tunnel; high-temperature gasdynamics; hypersonic aerodynamics and aerothermal dynamics
Prof. Dr. Yancheng You

E-Mail Website
Guest Editor
School of Aerospace Engineering, Xiamen University, Xiamen 361102, China
Interests: gasdynamics; shock waves; aerodynamic designs; oblique detonation
Dr. Zijian Zhang

E-Mail Website
Guest Editor
Department of Aeronautical and Aviation Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong
Interests: hypersonic air-breathing propulsion; detonation; supersonic combustion; high-speed multiphase flow; supersonic/hypersonic wind-tunnel experiment

Special Issue Information

Dear Colleagues,

Detonative propulsion represents the new generation of hypersonic propulsion techniques. Research in its field is booming and many advances have been made globally in recent years. The aim of this Special Issue is to publish these cutting-edge research results to promote the development of detonative propulsion and the cooperation of researchers in this field.

The topics for this Special Issue are broad, including (but not limited to)

  • oblique detonation engines,
  • rotating detonation engines,
  • pulsed detonation engines,
  • propulsive performance analysis of detonation engines,
  • the fundamental physics of gaseous detonation and multiphase detonation,
  • the design of detonation engines,
  • and all other research related to detonative propulsion techniques.

We invite authors to contribute new research results to this Special Issue.

Dr. Yunfeng Liu
Prof. Dr. Yancheng You
Dr. Zijian Zhang
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 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

  • oblique detonation engine
  • rotating detonation engine
  • pulsed detonation engine
  • propulsive performance analysis
  • gaseous detonation
  • multiphase detonation

Published Papers (4 papers)

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Research

19 pages, 9026 KiB  
Article
Computational Study of Fluidic-Valve Injectors for Detonation Engines
by Jayson Craig Small and Liwei Zhang
Aerospace 2024, 11(3), 171; https://doi.org/10.3390/aerospace11030171 - 21 Feb 2024
Viewed by 796
Abstract
The performance of detonation engines depends on propellant injectors. This study investigates a fluidic-valve injector mounted to a detonation tube. The injector is equipped with a recessed cavity connecting to the fuel plenum. After verifying the theoretical and numerical framework, three cases (I, [...] Read more.
The performance of detonation engines depends on propellant injectors. This study investigates a fluidic-valve injector mounted to a detonation tube. The injector is equipped with a recessed cavity connecting to the fuel plenum. After verifying the theoretical and numerical framework, three cases (I, II, and III) are analyzed, each representing different combinations of initial injector conditions and fuel supply setups. In all cases, a detonation wave is initiated near the headend of the detonation tube. It propagates through the initial section of the tube and undergoes diffraction and deformation at the flush-wall orifice. Among the considered cases, Case III, featuring a pre-pressurized initial injector flowfield and a total-pressure-inlet boundary, demonstrates the best agreement with the experimental results. It reveals a strong interaction between the longitudinally traveling detonation wave and the transverse propellant plume expanding from the orifice, causing the detonation wave to split. One part continues within the tube, while the other diffracts into the injector, creating a recirculation zone. Shock waves propagate within the injector and reflect at the base of the cavity, generating pressure spikes similar to the experimental observations. However, the contact surface separating the burnt products and fresh propellant reaches only a limited distance into the injector, suggesting a short interruption time and rapid recovery of the propellant supply. Full article
(This article belongs to the Special Issue Advances in Detonative Propulsion)
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23 pages, 8145 KiB  
Article
Numerical Investigation of Transverse-Jet-Assisted Initiation of Oblique Detonation Waves in a Combustor
by Zijian Zhang and Ziqi Jiang
Aerospace 2023, 10(12), 1033; https://doi.org/10.3390/aerospace10121033 - 14 Dec 2023
Viewed by 1017
Abstract
Detonation initiation is a prerequisite to normal operations of an oblique detonation engine (ODE), and initiation-assistant measures are imperative in cases of initiation failure that occur in a length-limited combustor under wide-range flight conditions. This study numerically investigates the initiation characteristics of oblique [...] Read more.
Detonation initiation is a prerequisite to normal operations of an oblique detonation engine (ODE), and initiation-assistant measures are imperative in cases of initiation failure that occur in a length-limited combustor under wide-range flight conditions. This study numerically investigates the initiation characteristics of oblique detonation waves (ODWs) in H2-fueled ODE combustors at wide-range flight Mach numbers Maf or flight altitudes Hf. Failures of ODW initiation are observed at both low Maf and high Hf if no measure is taken to assist initiation. Through analyses of the flow fields and theoretical predictions of the ignition induction length Lind, the data reveal that the detonation failure at low Maf is raised by the significant decrease in the post-shock temperature due to insufficient shock compression, leading to a significant increase in Lind. The detonation failure at high Hf is caused by the rapid decrease in the combustor inflow pressure as Hf increases, which also results in an increase in Lind. With further identifications of the key flow structures crucial to detonation initiation, an initiation-assistant concept employing a transverse H2 jet is proposed. The simulation results show that through an interaction between the incident oblique shock wave and the jet shock wave, the transverse jet helps to initiate an ODW in the combustor at a low Maf, and the initiation location is relatively fixed and determined by the jet location. At high Hf, a Mach reflection pattern is formed in the combustor under the effects of the transverse jet, and detonative combustion is achieved by the generated Mach stem and its reflected shock waves. The proposed concept of using transverse jets to assist detonation initiation provides a practical reference for future development of ODEs that are expected to operate under wide-range flight conditions. Full article
(This article belongs to the Special Issue Advances in Detonative Propulsion)
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28 pages, 11361 KiB  
Article
Mild Detonation Initiation in Rotating Detonation Engines: An Experimental Study of the Deflagration-to-Detonation Transition in a Semiconfined Flat Slit Combustor with Separate Supplies of Fuel and Oxidizer
by Igor O. Shamshin, Vladislav S. Ivanov, Viktor S. Aksenov, Pavel A. Gusev, Konstantin A. Avdeev and Sergey M. Frolov
Aerospace 2023, 10(12), 988; https://doi.org/10.3390/aerospace10120988 - 23 Nov 2023
Viewed by 968
Abstract
Rotating detonation engines (RDEs) are considered to be promising thrusters for aerospace propulsion. Detonation initiation in RDEs can be accompanied by a destructive explosion of an excess volume of the fuel mixture in the combustor. To exclude this phenomenon, a “mild” rather than [...] Read more.
Rotating detonation engines (RDEs) are considered to be promising thrusters for aerospace propulsion. Detonation initiation in RDEs can be accompanied by a destructive explosion of an excess volume of the fuel mixture in the combustor. To exclude this phenomenon, a “mild” rather than “strong” initiation of detonation is required. For the mild initiation of detonation in RDEs, it is necessary to ignite a mixture of a certain minimum volume sufficient for deflagration-to-detonation transition (DDT). In this study, the critical conditions for detonation initiation through DDT in a semiconfined slit combustor simulating the RDE combustor with a separate supply of ethylene and oxygen diluted with nitrogen (from 0 to 40%) were obtained experimentally. It turned out that for the mild initiation of detonation, it is necessary to ignite the mixture upon reaching the critical (minimum) height of the combustible mixture layer. Thus, for the mild initiation of detonation in the undiluted C2H4 + 3O2 mixture filling such a slit combustor, the height of the mixture layer must exceed the slit width by approximately a factor of 12. In terms of the transverse size of the detonation cell λ the minimum layer height of such mixtures in experiments is ~150λ. Compared to the experiments with the premixed composition, the critical height of the layer is 20% larger, which is explained by the finite rate of mixing. As the degree of oxygen dilution with nitrogen increases, the critical height of the layer increases, and the role of finite rate mixing decreases: the results no longer depend on the method of combustible mixture formation. Full article
(This article belongs to the Special Issue Advances in Detonative Propulsion)
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22 pages, 8443 KiB  
Article
Effect of Combustor Outlet Geometry on Operating Characteristics of Disk-Shaped Rotating Detonation Engine
by Zhenjuan Xia, Hu Ma, Gaoyang Ge, Yong He and Changsheng Zhou
Aerospace 2023, 10(8), 732; https://doi.org/10.3390/aerospace10080732 - 20 Aug 2023
Viewed by 1063
Abstract
A disk-shaped rotating detonation engine with H2/air mixture was tested to identify the impact of combustor outlet geometry on the engine’s operating characteristics. Three combustor outlet diameters and five outlet lengths are employed in the experiments. Results show that with the [...] Read more.
A disk-shaped rotating detonation engine with H2/air mixture was tested to identify the impact of combustor outlet geometry on the engine’s operating characteristics. Three combustor outlet diameters and five outlet lengths are employed in the experiments. Results show that with the increase of combustor convergent ratio, the propagation stability of the rotating detonation wave decreases, and the propagation velocity and pressure peak decrease slightly. When the convergent ratio increases to a certain value (1.70 in this study), a “platform zone” with a lower pressure value appears before the sharp rise of the dynamic pressure curve. The propagation mode varies with the increase of mass flow rate at different convergent ratios. As the mass flow rate increases, the wave head number in the combustor increases. But the change rule of propagation mode with mass flow rate is greatly affected by convergent ratio. Increasing the convergent ratio is conducive to the formation of multi-wave modes, and the critical mass flow rate for mode transition drops sharply. When the convergent ratio increases to 1.70, the unstable asymmetric dual-wave mode is obtained. With the increase in the convergent ratio, the engine’s operating range and operating stability decrease significantly. Finally, changing the combustor outlet length has little influence on the engine’s operating characteristics and detonation-wave parameters. Full article
(This article belongs to the Special Issue Advances in Detonative Propulsion)
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