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Advanced Propulsion System and Thermal Management Technology
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Advanced Propulsion System and Thermal Management Technology

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "J: Thermal Management".

Deadline for manuscript submissions: closed (31 December 2022) | Viewed by 12893

Printed Edition Available!
A printed edition of this Special Issue is available here.

Special Issue Editors

Dr. Jian Liu

E-Mail Website
Guest Editor
Research Institute of Aerospace Technology, Central South University, Changsha 410012, China
Interests: gas turbine; convective heat transfer; film cooling; transpiration cooling; scramjet; powder fuel; porous media; combustion; PIV; experimental heat transfer
Special Issues, Collections and Topics in MDPI journals
Dr. Chaoyang Liu

E-Mail Website
Guest Editor
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
Interests: supersonic flow and combustion
Special Issues, Collections and Topics in MDPI journals
Dr. Yiheng Tong

E-Mail Website
Guest Editor
Department of Aerospace Science and Technology, Space Engineering University. Beijing 100416, China
Interests: combustion instability and spray dynamics related to gas turbine and liquid rocket engines
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Bengt Sunden

E-Mail Website
Guest Editor
Department of Energy Sciences, Lund University, 221 00 Lund, Sweden
Interests: PEMFC; SOFC; batteries; hydrogen production and storage; renewable energy
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Propulsion systems still receive much research attention, especially aircraft engines, rocket engines and scramjets, etc. Some new propulsion systems are proposed that combine two basic propulsion systems, such as RBCC and TBCC, as well as new types of propulsion systems, such as combined space–air–ocean systems and highly integrated power systems, which can allow aircraft to fly safely from areas over land to those over the ocean. Propulsion systems are developed with the features of a wide speed range and long endurance, both for civil aircraft and military applications. Studies of propulsion systems mainly address their overall design, combustion, aerodynamics, internal flow and heat transfer, etc. High efficiency is pursued not only by optimized design but also via the development of suitable materials as well as the usage of powdered fuel.

Along with the development of high-efficiency propulsion systems, thermal management technology is also developed to address the increased heat from external aerodynamic heating and internal combustion heat at high speeds. This thermal management technology can transfer excessive heat to other low-temperature regions or provide thermal protection for structures via blade cooling in gas turbines and regenerative cooling in rocket engines. The thermal protection of engines is highly efficient due to the enhancement of convective heat transfer, such as the usage of superficial fluids, nanofluids, or newly designed roughened surfaces. Additionally, some heat transfer enhancement methods in heat exchangers, batteries and fuel cells are implemented in propulsion systems.

This Special Issue focuses on bringing together innovative developments in the fields of advanced propulsion systems and thermal management technology. Potential topics include, but are not limited to:

  • Propulsion system design;
  • Heat transfer enhancement;
  • Turbulent combustion;
  • Supercritical fluid;
  • Regenerative cooling;
  • Flow control;
  • Laser-based combustion diagnostics;
  • Spray dynamics;
  • Nanofluids;
  • Blade cooling;
  • Film cooling;
  • Transpiration cooling;
  • Multiphase flow;
  • Heat transfer in propulsion system;
  • Aerodynamics;
  • Combustion instability;
  • Powder fuel;
  • Spray dynamics;
  • Convective heat transfer;
  • Supersonic vehicles;
  • Thermal management in other fields.

Dr. Jian Liu
Dr. Chaoyang Liu
Dr. Yiheng Tong
Prof. Dr. Bengt Sunden
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

  • propulsion system
  • supersonic vehicles
  • heat transfer
  • combustion
  • turbulence flow
  • thermal protection
  • atomization
  • thermal acoustics
  • spray self-pulsation

Published Papers (8 papers)

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Editorial

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3 pages, 164 KiB  
Editorial
Heat Transfer Enhancement Methods Applied in Energy Conversion, Storage and Propulsion Systems
by Wenxiong Xi, Mengyao Xu, Kai Ma and Jian Liu
Energies 2022, 15(19), 7218; https://doi.org/10.3390/en15197218 - 01 Oct 2022
Viewed by 867
Abstract
With the development of energy storage and conversion or advanced propulsion systems, heat transfer enhancement methods have become widely applied [...] Full article
(This article belongs to the Special Issue Advanced Propulsion System and Thermal Management Technology)

Research

Jump to: Editorial, Other

13 pages, 8301 KiB  
Article
Fluidic Thrust, Propulsion, Vector Control of Supersonic Jets by Flow Entrainment and the Coanda Effect
by Toshihiko Shakouchi and Shunsuke Fukushima
Energies 2022, 15(22), 8513; https://doi.org/10.3390/en15228513 - 14 Nov 2022
Cited by 4 | Viewed by 2118
Abstract
Thrust, propulsion, vector control of supersonic jets has been applied to jet and rocket engines, ejectors, and other many devices. In general, there are two approaches to this type of control, namely mechanical moving systems and fluidic thrust vector control systems without moving [...] Read more.
Thrust, propulsion, vector control of supersonic jets has been applied to jet and rocket engines, ejectors, and other many devices. In general, there are two approaches to this type of control, namely mechanical moving systems and fluidic thrust vector control systems without moving parts, with mechanical moving systems being the most common. However, generally speaking, these systems are very complicated, and more simple methods and devices are desired. In this study, an extremely simple method for the thrust vector control of a supersonic jet by a fluidic Coanda nozzle (FC-nozzle) using the entrainment of the surrounding fluid and Coanda effect is newly proposed. The FC-nozzle consists of a pipe nozzle (Pi-nozzle), spacer, and linearly expanded Coanda nozzle (Co-nozzle) with eight suction pipes (Su-pipes) installed to surround the jet from the Pi-nozzle. The jet from the Pi-nozzle flows straight with the entrainment flow of the surrounding fluid. When some Su-pipes are closed, the pressure between the jet and Co-nozzle wall decreases, and subsequently, the jet deflects to the closed side of the Su-pipe and reattaches to the wall by the Coanda effect. The flow characteristics and deflection characteristics of the supersonic jet from the FC-nozzle are examined by the visualized flow pattern using the Schlieren method and measurements of the velocity distribution. As a result, it is shown that by changing the number of Su-pipes and the locations at which they are closed, the deflection angle and circumferential position of the jet from the Pi-nozzle can be easily controlled. Full article
(This article belongs to the Special Issue Advanced Propulsion System and Thermal Management Technology)
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18 pages, 8450 KiB  
Article
Numerical Simulation of Ventilation Performance in Mushroom Solar Greenhouse Design
by Yiming Li, Fujun Sun, Wenbin Shi, Xingan Liu and Tianlai Li
Energies 2022, 15(16), 5899; https://doi.org/10.3390/en15165899 - 14 Aug 2022
Cited by 2 | Viewed by 1594
Abstract
Numerical simulation is an effective tool for the thermal management of propulsion systems. Moreover, it contributes to the design and performance assessment of solar greenhouses for mushroom ventilation. Because the planning and design of the clustered solar greenhouse are still undiscovered, this study [...] Read more.
Numerical simulation is an effective tool for the thermal management of propulsion systems. Moreover, it contributes to the design and performance assessment of solar greenhouses for mushroom ventilation. Because the planning and design of the clustered solar greenhouse are still undiscovered, this study has developed a 3-D mathematical model suitable for a large-scale park of mushroom solar greenhouses based on computational fluid dynamics (CFD) theory. The effects of the orientation arrangement, horizontal spacing, vertical spacing of the cultivation racks, and the building distance between adjacent greenhouses on the ventilation performance were analyzed. The numerical simulation showed good agreement with the experimental measurement. The CFD results indicated that the reasonable layout of cultivation racks in mushroom solar greenhouses is a north-south arrangement. The horizontal spacing of cultivation racks has a significant influence on the wind speed and cooling rate, and the optimal spacing is 0.8 m. The overall height of the cultivation racks has little effect on the ventilation performance. Nevertheless, the vertical spacing between cultivation rack layers has a remarkable effect, and the optimal vertical spacing is 0.29 m. Reducing the building distance between the two adjacent greenhouses within a certain range helps increase the ventilation efficiency, leading to an increase in land utilization in the greenhouse park. The optimal building distance between the adjacent greenhouses is 10 m. The research results can provide theoretical guidance for improving the production quality and land utilization of mushroom facilities. Full article
(This article belongs to the Special Issue Advanced Propulsion System and Thermal Management Technology)
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15 pages, 5078 KiB  
Article
Parametric Study on Thermo-Hydraulic Performance of NACA Airfoil Fin PCHEs Channels
by Wei Wang, Liang Ding, Fangming Han, Yong Shuai, Bingxi Li and Bengt Sunden
Energies 2022, 15(14), 5095; https://doi.org/10.3390/en15145095 - 12 Jul 2022
Cited by 5 | Viewed by 1641
Abstract
In this work, a discontinuous airfoil fin printed circuit heat exchanger (PCHE) was used as a recuperator in a micro gas turbine system. The effects of the airfoil fin geometry parameters (arc height, maximum arc height position, and airfoil thickness) and the airfoil [...] Read more.
In this work, a discontinuous airfoil fin printed circuit heat exchanger (PCHE) was used as a recuperator in a micro gas turbine system. The effects of the airfoil fin geometry parameters (arc height, maximum arc height position, and airfoil thickness) and the airfoil fin arrangements (horizontal and vertical spacings) on the PCHE channel’s thermo-hydraulic performance were extensively examined by a numerical parametric study. The flow features, local heat transfer coefficient, and wall shear stress were examined in detail to obtain an enhanced heat transfer mechanism for a better PCHE design. The results show that the heat transfer and flow resistance were mainly increased at the airfoil leading edge owing to a flow jet, whereas the airfoil trailing edge had little effect on the thermo-hydraulic performance. The airfoil thickness was the most significant while the arc height and the vertical spacing were moderately significant to the performance. Moreover, only the airfoil thickness had a significant effect on the PCHE compactness. Based on a comprehensive investigation, two solutions NACA-6230 and -3220 were selected owing to their better thermal performance and smaller pressure drop, respectively, with horizontal spacings of 2 mm and vertical spacings of 2 or 3 mm. Full article
(This article belongs to the Special Issue Advanced Propulsion System and Thermal Management Technology)
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26 pages, 12504 KiB  
Article
Numerical Study of the Effect of the Rolling Motion on the Subcooled Flow Boiling in the Subchannel
by Yaru Li, Xiangyu Chi, Zezhao Nan, Xuan Yin, Xiaohan Ren and Naihua Wang
Energies 2022, 15(13), 4866; https://doi.org/10.3390/en15134866 - 02 Jul 2022
Cited by 1 | Viewed by 1028
Abstract
The marine environment may change the force on the fluid and inevitably influence bubble behavior and the two-phase flow in the reactor core, which are vital to the safety margin of a nuclear reactor. To explore the effect of the marine motion on [...] Read more.
The marine environment may change the force on the fluid and inevitably influence bubble behavior and the two-phase flow in the reactor core, which are vital to the safety margin of a nuclear reactor. To explore the effect of the marine motion on the flow and heat transfer features of subcooled flow boiling in the reactor core, the volume of fluid (VOF) method is employed to reveal the interaction between the interface structure and two-phase flow in the subchannel under rolling motion. The variations of several physical parameters are obtained, including the transverse flow, the vapor volume fraction, the vapor adhesion ratio, and the phase distribution of boiling two-phase flow with time. Sensitivity analyses of the amplitude and the period of the rolling motion were performed to demonstrate the mechanisms of the influence of the rolling motion. We found that the transverse flow in the subchannel was mainly affected by the Euler force under the rolling motion. In contrast to the two-phase flow in the static state, the vapor volume fraction and vapor adhesion ratio show different characteristics under rolling motion. Additionally, the onset of significant void (OSV) point changes periodically under rolling motion. Full article
(This article belongs to the Special Issue Advanced Propulsion System and Thermal Management Technology)
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18 pages, 6572 KiB  
Article
Improved Body Force Model for Estimating Off-Design Axial Compressor Performance
by Jia Huang, Yongzhao Lv, Aiguo Xia, Shengliang Zhang, Wei Tuo, Hongtao Xue, Yantao Sun and Xiuran He
Energies 2022, 15(12), 4389; https://doi.org/10.3390/en15124389 - 16 Jun 2022
Cited by 3 | Viewed by 1243
Abstract
Based on the COMSOL software, body forces substituted into the Reynolds-averaged Navier–Stokes (RANS) equations as the source terms instead of the actual blade rows were improved to better predict the compressor performance. Improvements in parallel body force modeling were implemented, central to which [...] Read more.
Based on the COMSOL software, body forces substituted into the Reynolds-averaged Navier–Stokes (RANS) equations as the source terms instead of the actual blade rows were improved to better predict the compressor performance. Improvements in parallel body force modeling were implemented, central to which were the local flow quantities. This ensured accurate and reliable off-design performance prediction. The parallel force magnitude mainly depended on the meridional entropy gradient extracted from three-dimensional (3D) steady single-passage RANS solutions. The COMSOL software could easily and accurately translate the pitchwise-averaged entropy into the grid points of the body force domain. A NASA Rotor 37 was used to quantify the improved body force model to represent the compressor. Compared with the previous model, the improved body force model was more efficient for the numerical calculations, and it agreed well with the experimental data and computational fluid dynamics (CFD) results. The results indicate that the improved body force model could quickly and efficiently capture the flow field through a turbomachinery blade row. Full article
(This article belongs to the Special Issue Advanced Propulsion System and Thermal Management Technology)
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14 pages, 4793 KiB  
Article
Generation and Propagation Characteristics of an Auto-Ignition Flame Kernel Caused by the Oblique Shock in a Supersonic Flow Regime
by Wenxiong Xi, Mengyao Xu, Chaoyang Liu, Jian Liu and Bengt Sunden
Energies 2022, 15(9), 3356; https://doi.org/10.3390/en15093356 - 05 May 2022
Cited by 1 | Viewed by 1661
Abstract
The auto-ignition caused by oblique shocks was investigated experimentally in a supersonic flow regime, with the incoming flow at a Mach number of 2.5. The transient characteristics of the auto-ignition caused by shock evolvements were recorded with a schlieren photography system, and the [...] Read more.
The auto-ignition caused by oblique shocks was investigated experimentally in a supersonic flow regime, with the incoming flow at a Mach number of 2.5. The transient characteristics of the auto-ignition caused by shock evolvements were recorded with a schlieren photography system, and the initial flame kernel generation and subsequent propagation were recorded using a high-speed camera. The fuel mixing characteristics were captured using NPLS (nanoparticle-based planar laser scattering method). This work aimed to reveal the flame spread mechanism in a supersonic flow regime. The effects of airflow total temperature, fuel injection pressure, and cavity length in the process of auto-ignition and on the auto-ignitable boundary were investigated and analyzed. From this work, it was found that the initial occurrence of auto-ignition is first induced by oblique shocks and then propagated upstream to the recirculation region, to establish a sustained flame. The auto-ignition performance can be improved by increasing the injection pressure and airflow total temperature. In addition, a cavity with a long length has benefits in controlling the flame spread from the induced state to a sustained state. The low-speed recirculating region created in the cavity is beneficial for the flame spread, which has the function of flame-holding and prevents the flame from being blown away. Full article
(This article belongs to the Special Issue Advanced Propulsion System and Thermal Management Technology)
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Other

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8 pages, 1713 KiB  
Perspective
Progress of Coupled Heat Transfer Mechanisms of Regenerative Cooling System in a Scramjet
by Ni He, Chaoyang Liu, Yu Pan and Jian Liu
Energies 2023, 16(3), 1025; https://doi.org/10.3390/en16031025 - 17 Jan 2023
Cited by 2 | Viewed by 1396
Abstract
The feasibility of regenerative cooling technology in scramjet engines has been verified, while the heat transfer behavior involved in the process needs further study. This paper expounds on the necessity of coupled heat-transfer analysis and summarizes its research progress. The results show that [...] Read more.
The feasibility of regenerative cooling technology in scramjet engines has been verified, while the heat transfer behavior involved in the process needs further study. This paper expounds on the necessity of coupled heat-transfer analysis and summarizes its research progress. The results show that the effect of pyrolysis on heat transfer in the cooling channel depends on the heat flux and coking rate, and the coupling relationship between combustion and heat transfer is closely related to the fuel flow rate. Therefore, we confirm that regulating the cooling channel layout according to the real heat-flux distribution, suppressing coking, and accurately controlling the fuel flow rate can contribute to accomplishing the optimal collaborative design of cooling performance and combustion performance. Finally, a conjugate thermal analysis model can be used to evaluate the performance of various thermal protection systems. Full article
(This article belongs to the Special Issue Advanced Propulsion System and Thermal Management Technology)
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