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Aerospace
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Supersonic Combustion in Scramjet Engine
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Supersonic Combustion in Scramjet Engine

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

Deadline for manuscript submissions: 30 April 2024 | Viewed by 4910

Special Issue Editors

Prof. Dr. Jeong Yeol Choi

E-Mail Website
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
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Hyoung Jin Lee

E-Mail Website
Guest Editor
Department of Aerospace Engineering, Inha University, Incheon 21999, Republic of Korea
Interests: ram & scram jet; missile system; hypersonic flows; high speed combustion

Special Issue Information

Dear Colleagues,

Powered hypersonic flight is no longer a dream, but rather, a reality. It has been made possible by several decades of efforts and devotion from our senior colleagues. Nevertheless, it is just the beginning. As always in all engineering fields, continuing innovations at the present level mature the technology from a prototype to military use and then, finally, to civil applications at an affordable cost.

Supersonic combustion in scramjet engines lies at the core of the technologies for powered hypersonic flight. For this Special Issue, authors are invited to contribute high-quality original papers covering the fundamental physics of supersonic combustion, and new developments in technology for scramjet engines. We also welcome papers discussing new theoretical, analytical, experimental, and numerical methods and techniques useful for further understanding and development of supersonic combustion in scramjet engines.

Prof. Dr. Jeong Yeol Choi
Prof. Dr. Hyoung Jin Lee
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

  • supersonic combustion
  • scramjet engine
  • fundamental physics
  • new developments
  • experimental techniques
  • numerical methods

Published Papers (3 papers)

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Research

34 pages, 31614 KiB  
Article
Reactive Flow Dynamics of Low-Frequency Instability in a Scramjet Combustor
by Seung-Min Jeong, Hyung-Seok Han, Bu-Kyeng Sung, Wiedae Kim and Jeong-Yeol Choi
Aerospace 2023, 10(11), 932; https://doi.org/10.3390/aerospace10110932 - 31 Oct 2023
Cited by 1 | Viewed by 1043
Abstract
This study numerically investigated the combustion instability and characteristics of a laboratory-scale gaseous hydrogen-fueled scramjet combustor. For this purpose, a numerical simulation with an improved detached eddy simulation and a detailed hydrogen/oxygen reaction mechanism was performed. The numerical framework used high-resolution schemes with [...] Read more.
This study numerically investigated the combustion instability and characteristics of a laboratory-scale gaseous hydrogen-fueled scramjet combustor. For this purpose, a numerical simulation with an improved detached eddy simulation and a detailed hydrogen/oxygen reaction mechanism was performed. The numerical framework used high-resolution schemes with high-order accuracy to ensure high resolution and fidelity. A total of five fuel injection pressures were considered to characterize the combustion instability as a function of the equivalence ratio. A sampling time of up to 100 ms was considered to sufficiently accumulate several cycles of low-frequency combustion instability dynamics with a period in the order of 100 Hz. Numerical results revealed the repetitive formation/dissipation dynamics of the upstream-traveling shock wave, and it acts as a key factor of combustion instability. The period and derived principal frequency of these upstream-traveling shock waves is several ms. The frequency analysis showed that the instability frequency increased in the low-frequency range as the combustion mode transitioned from the cavity shear-layer to the jet-wake type. This characteristic was derived from the transition in combustion mode at the same equivalence ratio. Therefore, it suggests that the instability frequency shifting is governed by the combustion mode rather than the equivalence ratio. These comprehensive numerical results demonstrated not only the effect of the equivalence ratio but also the important role of the combustion mode on the low-frequency combustion instability. Full article
(This article belongs to the Special Issue Supersonic Combustion in Scramjet Engine)
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21 pages, 9116 KiB  
Article
Experimental Study on the Ignition Characteristics of Scramjet Combustor with Tandem Cavities Using Micro-Pulse Detonation Engine
by Min-Su Kim, In-Hoi Koo, Keon-Hyeong Lee, Eun-Sung Lee, Hyung-Seok Han, Seung-Min Jeong, Holak Kim and Jeong-Yeol Choi
Aerospace 2023, 10(8), 706; https://doi.org/10.3390/aerospace10080706 - 11 Aug 2023
Cited by 2 | Viewed by 1269
Abstract
This experimental investigation focused on the ignition and combustion characteristics of a tandem cavity-based scramjet combustor with side-by-side identical cavities. This study utilized the Pusan National University-direct connect scramjet combustor (PNU-DCSC), which was capable of simulating flight conditions at Mach number 4.0–5.0 and [...] Read more.
This experimental investigation focused on the ignition and combustion characteristics of a tandem cavity-based scramjet combustor with side-by-side identical cavities. This study utilized the Pusan National University-direct connect scramjet combustor (PNU-DCSC), which was capable of simulating flight conditions at Mach number 4.0–5.0 and altitudes of 20–25 km using the vitiated air heater (VAH). The combustion tests were conducted under off-design point conditions corresponding to low inlet enthalpy. It is a condition in which self-ignition does not occur, and a micro pulse detonation engine (μPDE) ignitor is used. The results revealed that as the injection pressure of the gaseous hydrogen fuel (GH2) and the corresponding equivalence ratio increased, the combustion mode transitioned from the cavity-shear layer flame to the jet-wake flame. Furthermore, the measured wall static pressure profiles along the isolator and scramjet combustor indicated that the region of elevated pressure distribution caused by the shock train expanded upstream with higher equivalence ratios. When ignited from the secondary cavity, the combustion area did not extend to the primary cavity at lower equivalence ratios, while it expanded upstream faster with higher equivalence ratios. Therefore, the combustion characteristics of the tandem cavity were found to vary based on the overall equivalence ratio of the main fuel (GH2) and ignition position. Full article
(This article belongs to the Special Issue Supersonic Combustion in Scramjet Engine)
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15 pages, 18493 KiB  
Article
A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition
by Jae-Hyuk Lee, Eun-Sung Lee, Hyung-Seok Han, Min-Su Kim and Jeong-Yeol Choi
Aerospace 2023, 10(5), 415; https://doi.org/10.3390/aerospace10050415 - 28 Apr 2023
Cited by 6 | Viewed by 1589
Abstract
Vitiation air heater (VAH) combustion characteristics for a direct-connect scramjet combustor (DCSC) were experimentally studied. The VAH consists of a head, modular chamber, and circular-to-rectangular shape transition (CRST) nozzle. The CRST nozzle transforms the circular cross-sectioned rocket-type VAH into a rectangular cross-sectioned scramjet [...] Read more.
Vitiation air heater (VAH) combustion characteristics for a direct-connect scramjet combustor (DCSC) were experimentally studied. The VAH consists of a head, modular chamber, and circular-to-rectangular shape transition (CRST) nozzle. The CRST nozzle transforms the circular cross-sectioned rocket-type VAH into a rectangular cross-sectioned scramjet combustor. The CRST nozzle exit Mach numbers at the top, middle, and bottom were measured using a tungsten wedge. The oblique shock formed by the wedge was captured using Schlieren visualization and recorded with a high-speed camera. The θ-β-M relation showed that the exit Mach number was 2.04 ± 0.04 with a chamber pressure of 1.685 ± 0.07 MPa. With the VAH design point verified, preliminary scramjet combustor ignition tests were conducted. As the fuel was not auto-ignited by the vitiated air, the forced ignition method, in which VAH ignition flame ignites the scramjet fuel, was used. The Schlieren images showed that a cavity shear layer combustion mode was formed and also showed that the forced ignition method could be used as a reference model for the ignitor-ignition method. Full article
(This article belongs to the Special Issue Supersonic Combustion in Scramjet Engine)
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