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Special Issue "Combustion for Aerospace Propulsion"

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

Deadline for manuscript submissions: closed (15 March 2011)

Special Issue Editor

Guest Editor
Prof. Dr. Vasily Novozhilov

Centre for Environmental Safety and Risk Engineering (CESARE), Victoria University, Room 4203, Level 2, Building 4, Hoppers Lane, Werribee, VIC 3030, Australia
Website | E-Mail
Phone: 61 3 9919 8612
Fax: (61) 3 9919 8058
Interests: fire safety science; combustion; heat transfer; computational fluid dynamics; applied mathematics Contribution: Special Issue: Combustion for Aerospace Propulsion

Special Issue Information

Dear Colleagues,

The present issue focuses on fundamentals of combustion processes in aerospace applications, and implementation of relevant technologies. Combustion is a key technology of utilising chemical energy for propulsion. Significant progress has been made in this field in understanding and ability to model combustion, on one hand, and development of innovative technologies on the other hand. The volume seeks to bring together both fundamental and applied papers in order to show how interaction between science and technology can lead to introduction of highly efficient propulsion systems. Examples of specific applications include Turbopropulsion; Solid, Liquid and Hybrid Rocket Motors. Contributions covering prospective technologies, such as Supersonic Combustion Ramjet (SCRJ) engines, and Pulse Detonation engines, are especially welcome. Fundamentals of combustion and fluid dynamics will cover areas such as Turbulent Combustion, Combustion Control, Combustion Instabilities, Pulse Detonation, Combustion Modeling, Atomization and Spray Combustion, Swirling Flows, and others. Of high importance is the issue of material behavior under relevant combustion conditions. Therefore, areas such as propellant combustion, and solid fuel combustion (for hybrid propulsion applications) will be considered. Original and review papers are sought for this volume, which are of theoretical, computational or experimental nature. The papers can also report design methodologies, testing procedures, as well as other relevant issues.

Prof. Dr. Vasily Novozhilov
Guest Editor

Keywords

  • turbopropulsion
  • rocket engines
  • scramjet engines
  • pulse detonation
  • turbulent combustion

Published Papers (3 papers)

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Research

Open AccessArticle Polymer Combustion as a Basis for Hybrid Propulsion: A Comprehensive Review and New Numerical Approaches
Energies 2011, 4(10), 1779-1839; doi:10.3390/en4101779
Received: 28 July 2011 / Revised: 11 October 2011 / Accepted: 12 October 2011 / Published: 24 October 2011
Cited by 3 | PDF Full-text (2314 KB) | HTML Full-text | XML Full-text
Abstract
Hybrid Propulsion is an attractive alternative to conventional liquid and solid rocket motors. This is an active area of research and technological developments. Potential wide application of Hybrid Engines opens the possibility for safer and more flexible space vehicle launching and manoeuvring. The
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Hybrid Propulsion is an attractive alternative to conventional liquid and solid rocket motors. This is an active area of research and technological developments. Potential wide application of Hybrid Engines opens the possibility for safer and more flexible space vehicle launching and manoeuvring. The present paper discusses fundamental combustion issues related to further development of Hybrid Rockets. The emphasis is made on the two aspects: (1) properties of potential polymeric fuels, and their modification, and (2) implementation of comprehensive CFD models for combustion in Hybrid Engines. Fundamentals of polymeric fuel combustion are discussed. Further, steps necessary to accurately describe their burning behaviour by means of CFD models are investigated. Final part of the paper presents results of preliminary CFD simulations of fuel burning process in Hybrid Engine using a simplified set-up. Full article
(This article belongs to the Special Issue Combustion for Aerospace Propulsion)
Open AccessArticle Scale Effects on Solid Rocket Combustion Instability Behaviour
Energies 2011, 4(1), 90-107; doi:10.3390/en4010090
Received: 8 December 2010 / Revised: 13 December 2010 / Accepted: 29 December 2010 / Published: 11 January 2011
Cited by 5 | PDF Full-text (516 KB) | HTML Full-text | XML Full-text
Abstract
The ability to understand and predict the expected internal behaviour of a given solid-propellant rocket motor under transient conditions is important. Research towards predicting and quantifying undesirable transient axial combustion instability symptoms necessitates a comprehensive numerical model for internal ballistic simulation under dynamic
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The ability to understand and predict the expected internal behaviour of a given solid-propellant rocket motor under transient conditions is important. Research towards predicting and quantifying undesirable transient axial combustion instability symptoms necessitates a comprehensive numerical model for internal ballistic simulation under dynamic flow and combustion conditions. A numerical model incorporating pertinent elements, such as a representative transient, frequency-dependent combustion response to pressure wave activity above the burning propellant surface, is applied to the investigation of scale effects (motor size, i.e., grain length and internal port diameter) on influencing instability-related behaviour in a cylindrical-grain motor. The results of this investigation reveal that the motor’s size has a significant influence on transient pressure wave magnitude and structure, and on the appearance and magnitude of an associated base pressure rise. Full article
(This article belongs to the Special Issue Combustion for Aerospace Propulsion)
Open AccessArticle Scale Effects on Quasi-Steady Solid Rocket Internal Ballistic Behaviour
Energies 2010, 3(11), 1790-1804; doi:10.3390/en3111790
Received: 23 October 2010 / Revised: 4 November 2010 / Accepted: 11 November 2010 / Published: 15 November 2010
PDF Full-text (321 KB) | HTML Full-text | XML Full-text
Abstract
The ability to predict with some accuracy a given solid rocket motor’s performance before undertaking one or several costly experimental test firings is important. On the numerical prediction side, as various component models evolve, their incorporation into an overall internal ballistics simulation program
[...] Read more.
The ability to predict with some accuracy a given solid rocket motor’s performance before undertaking one or several costly experimental test firings is important. On the numerical prediction side, as various component models evolve, their incorporation into an overall internal ballistics simulation program allows for new motor firing simulations to take place, which in turn allows for updated comparisons to experimental firing data. In the present investigation, utilizing an updated simulation program, the focus is on quasi-steady performance analysis and scale effects (influence of motor size). The predicted effects of negative/positive erosive burning and propellant/casing deflection, as tied to motor size, on a reference cylindrical-grain motor’s internal ballistics, are included in this evaluation. Propellant deflection has only a minor influence on the reference motor’s internal ballistics, regardless of motor size. Erosive burning, on the other hand, is distinctly affected by motor scale. Full article
(This article belongs to the Special Issue Combustion for Aerospace Propulsion)

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