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Energies
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Advancements in Energy-Efficient Propulsion Systems for Aerospace Applications
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Advancements in Energy-Efficient Propulsion Systems for Aerospace Applications

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "I2: Energy and Combustion Science".

Deadline for manuscript submissions: closed (20 November 2024) | Viewed by 1369

Special Issue Editors

Dr. Maria Grazia De Giorgi

E-Mail Website
Guest Editor
Department of Engineering for Innovation, University of Salento, Via per Monteroni, 73100 Lecce, Italy
Interests: sustainable aviation; aerospace propulsion; hydrogen combustion; ammonia combustion; plasma-assisted combustion
Special Issues, Collections and Topics in MDPI journals
Dr. Guido Marseglia

E-Mail Website
Guest Editor
Department of Engineering for Innovation, University of Salento, Via per Monteroni, 73100 Lecce, Italy
Interests: combustion; micropropulsion; microchannels
Dr. Elisa Pescini

E-Mail Website
Guest Editor
Centro Universitario de la Defensa, Universidad Politécnica de Cartagena, C/Coronel López Peña S/N, Santiago de La Ribera, 30720 Murcia, Spain
Interests: active flow; combustion control

Special Issue Information

Dear Colleagues,

This Special Issue aims to provide an in-depth overview of the latest advancements and research in energy-efficient propulsion systems for aerospace applications. Topics of interest include innovations in rocket and jet engines, electric and hybrid propulsion, sustainable and green propulsion technologies, and advanced modelling and experimental techniques for the characterization of propulsion systems. Original research articles, review papers, and case studies that explore theoretical, experimental, and applied aspects of energy-efficient aerospace propulsion are welcome.

Authors are encouraged to submit manuscripts that address these themes, contributing to the collective understanding and progression of energy-efficient propulsion technologies in the field of aerospace. This Special Issue intends to showcase cutting-edge developments, encourage interdisciplinary collaboration, and promote sustainable solutions within the aerospace industry, focusing on reducing the environmental impact as well as enhancing the efficiency and effectiveness of propulsion systems.

Dr. Maria Grazia De Giorgi
Dr. Guido Marseglia
Dr. Elisa Pescini
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. Energies is an international peer-reviewed open access semimonthly 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 2600 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

  • rocket engines
  • jet engines
  • electric propulsion
  • hybrid propulsion
  • green propulsion technologies
  • sustainable aerospace propulsion
  • advanced materials
  • theoretical propulsion research
  • experimental propulsion research
  • applied propulsion technologies
  • aerospace propulsion innovations
  • propulsion system optimization
  • high-efficiency propulsion
  • space propulsion systems

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Published Papers (1 paper)

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Research

14 pages, 3950 KiB  
Article
Ground Testing of a Miniature Turbine Jet Engine for Specific Flight Conditions
by Ryszard Chachurski, Łukasz Omen, Andrzej J. Panas and Piotr Zalewski
Energies 2025, 18(1), 73; https://doi.org/10.3390/en18010073 - 28 Dec 2024
Viewed by 868
Abstract
This paper presents the design and development project of an engine test stand specifically constructed for ground testing of miniature turbine jet engines (MTJEs) along with conclusive results of the conducted investigations. The tested engines serve as the propulsion system for an unmanned [...] Read more.
This paper presents the design and development project of an engine test stand specifically constructed for ground testing of miniature turbine jet engines (MTJEs) along with conclusive results of the conducted investigations. The tested engines serve as the propulsion system for an unmanned aerial vehicle (UAV) platform. The engine test stand was used to determine various operating parameters of the engine, with a particular focus on recording variations and changes in temperature and pressure at the engine control cross-sections: behind the compressor, the combustion chamber, and at the final cross-section of the nozzle. The analysis of the direct test results allowed the evaluation of the engine’s behavior under hydration conditions and documents the quantitative and qualitative response of the control system of the engine. Of particular interest are the results showing an increase in exhaust system temperature with a decrease in the temperature in combustion chamber under hydrated conditions. The test program assumed and considered the acting loads and forces in both standard and specific flight conditions, including scenarios for a heavy rain. The preliminary evaluation of the investigation results provided data and insights required for further analysis. Quantitatively, the measured temperature value in the exhaust system does not exceed 700 °C and the temperature increase resulting from the introduction of water and the engine’s response to the out-of-operation event is approximately 50 °C for the JetCat 140. Qualitatively different effects were observed in the combustion moment, consisting in a drop in temperature values during the introduction of water into the engine flow channel. The introduction of water into the GTM 140 inlet revealed no significant changes in the variations of pressure and temperature measured in selected engine design sections. Based on the knowledge and experience gained, a fully operational test stand to monitor the parameters and performance of the MTJEs, which are used for aerial target propulsion, was developed. Full article
(This article belongs to the Special Issue Advancements in Energy-Efficient Propulsion Systems for Aerospace Applications)
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