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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: closed (30 April 2024) | Viewed by 6290

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

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Published Papers (3 papers)

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Research

15 pages, 9259 KiB  
Article
Experimental Investigation of Pulse Detonation Combustion Characteristics via Atomizer Geometry
by Yoojin Oh, Myeung Hwan Choi and Sungwoo Park
Aerospace 2024, 11(9), 776; https://doi.org/10.3390/aerospace11090776 - 20 Sep 2024
Viewed by 1004
Abstract
Recent studies have increasingly focused on integrating detonation processes into engine technologies, advancing beyond the fundamental research phase of detonation research. The present study investigates the detonability and combustion characteristics of liquid fuels, specifically ethanol, with an emphasis on the effects of atomization [...] Read more.
Recent studies have increasingly focused on integrating detonation processes into engine technologies, advancing beyond the fundamental research phase of detonation research. The present study investigates the detonability and combustion characteristics of liquid fuels, specifically ethanol, with an emphasis on the effects of atomization properties facilitated by different atomizer designs to implement pulse detonation combustion engines. Oxygen was used as the oxidizer. We employed internal injectors (I45, I90, IB4) and atomizer venturis (VA, VB, VR) to examine how variations in liquid fuel atomization and atomizer configurations influence detonation. The occurrence of detonation was assessed using predicted Sauter mean diameters (SMDs) and exit velocities for different atomizer setups. Additionally, we evaluated the effects of nitrogen dilution at concentrations of 0%, 25%, and 50% on velocity variations and changes in detonation characteristics. The findings suggest that while higher exit velocities decrease SMD, facilitating detonation, excessively high velocities hinder detonation initiation. Conversely, lower exit velocities emphasize the role of SMD in initiating detonation. However, the introduction of nitrogen, which reduces the SMD, was found to decrease reactivity and impede detonation. Full article
(This article belongs to the Special Issue Supersonic Combustion in Scramjet Engine)
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16 pages, 7306 KiB  
Article
Investigation of Spray Characteristics for Detonability: A Study on Liquid Fuel Injector and Nozzle Design
by Myeung Hwan Choi, Yoojin Oh and Sungwoo Park
Aerospace 2024, 11(6), 421; https://doi.org/10.3390/aerospace11060421 - 23 May 2024
Cited by 1 | Viewed by 1021
Abstract
Detonation engines are gaining prominence as next-generation propulsion systems that can significantly enhance the efficiency of existing engines. This study focuses on developing an injector utilizing liquid fuel and a gas oxidizer for application in detonation engines. In order to better understand the [...] Read more.
Detonation engines are gaining prominence as next-generation propulsion systems that can significantly enhance the efficiency of existing engines. This study focuses on developing an injector utilizing liquid fuel and a gas oxidizer for application in detonation engines. In order to better understand the spray characteristics suitable for the pulse detonation engine (PDE) system, an injector was fabricated by varying the Venturi nozzle exit diameter ratio and the geometric features of the fuel injection hole. Analysis of high-speed camera images revealed that the Venturi nozzle exit diameter ratio plays a crucial role in determining the characteristics of air-assist or air-blast atomization. Under the conditions of an exit diameter ratio of Re/Ri = 1.0, the formation of a liquid film at the exit was observed, and it was identified that the film’s length is influenced by the geometric characteristics of the fuel injection hole. The effect of the fuel injection hole and Venturi nozzle exit diameter ratio on SMD was analyzed by using droplet diameter measurement. The derived empirical correlation indicates that the atomization mechanism varies depending on the Venturi nozzle exit diameter ratio, and it also affects the distribution of SMD. The characteristics of the proposed injector, its influence on SMD, and its velocity, provide essential groundwork and data for the design of detonation engines employing liquid fuel. 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 9 | Viewed by 2795
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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