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Energies
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Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion
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Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "J2: Thermodynamics".

Deadline for manuscript submissions: closed (18 August 2023) | Viewed by 11464

Special Issue Editors

Dr. Zhaoxin Ren

E-Mail Website
Guest Editor
1. Zienkiewicz Centre for Computational Engineering, Faculty of Science and Engineering, Swansea University, Swansea SA1 8EN, UK
2. Department of Aerospace Engineering, Swansea University, Swansea SA1 8EN, UK
Interests: hydrogen for sustainable aviation; pressure gain combustion; CFD; supersonic/multiphase/reactive/cryogenic flow
Special Issues, Collections and Topics in MDPI journals
Dr. Qiaofeng Xie

E-Mail Website
Guest Editor
School of Aerospace Engineering, Tsinghua University, Beijing 100084, China
Interests: combustion and detonation for aerospace propulsion
Dr. Jie Lu

E-Mail Website
Guest Editor
School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China
Interests: flow and combustion in aero engine

Special Issue Information

Dear Colleagues,

We kindly invite you to contribute an article to the Special Issue of the MDPI journal Energies on the topic “Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion”. An understanding of the heat transfer, fluid dynamics, and combustion process via the utilization of theoretical analysis, experiments, and numerical simulations is important for the engineering application of next-generation energy and propulsion systems. This Special Issue focuses on the mechanisms of complex heat and thermal fluid flow, and the associated control methods for advanced aeroengines, such as combined cycle engines, scramjet engines, and detonation engines.

Potential topics include but are not limited to the following:

  • Thermal analysis of advanced aeroengines;
  • Mathematical modeling and numerical simulation of heat and thermal fluid flow;
  • Multiphase flow and heat and mass transfer;
  • Test and measurement technology of flow and combustion process;
  • Heating and cooling methods of advanced engines;
  • Control and organization methods for flow and combustion;
  • New propellant technology for aerospace propulsion.

Dr. Zhaoxin Ren
Dr. Qiaofeng Xie
Dr. Jie Lu
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

  • Turbulent flow
  • Multiphase flow
  • Reacting flow
  • Heat transfer
  • Combustion
  • Aeroengine
  • Thermal analysis
  • Experiment
  • Numerical simulation
  • Engine control

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Published Papers (6 papers)

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Research

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18 pages, 24883 KiB  
Article
Study of Particle Size Measurement by the Extinction Method in Flame
by Hengsheng Xiang, Bo Cheng, Chengfei Zhang and Wensheng Qiao
Energies 2023, 16(12), 4792; https://doi.org/10.3390/en16124792 - 19 Jun 2023
Cited by 1 | Viewed by 1234
Abstract
The laser extinction method (LEM) is particularly suitable for measuring particle sizes in flames because this method, which is based on the Beer–Lambert law, is non-intrusive and easy to implement. In the LEM, the interpretation of the extinction data is usually developed under [...] Read more.
The laser extinction method (LEM) is particularly suitable for measuring particle sizes in flames because this method, which is based on the Beer–Lambert law, is non-intrusive and easy to implement. In the LEM, the interpretation of the extinction data is usually developed under the assumption that light extinction due to scattering is a result of the superposition of single scattering by individual particles; however, this could be violated for flames with dense concentrations of particles in which multiple scattering could occur. Quantifying the effect of multiple scattering under general conditions is still a formidable problem. In this work, we carried out a series of careful measurements of the laser extinction using standard particles of various known sizes, number densities and optical path lengths, all under the condition that the acceptance angle of the detector was limited to nearly zero. Combined with a four-flux model, we quantitatively analyzed the effect of multiple scattering on the size measurement using the LEM. The results show that the effect of multiple scattering could be ignored when the optical thickness is less than two under strict restrictions on the detector acceptance angle. Guided by this, the size distribution of an alumina (Al2O3) particle sample was measured by the LEM with dual wavelengths. Parameterized distributions were solved with the help of graph plotting, and the results compared well with the measurement from the Malvern particle size analyzer. The same method was then used to measure the particle size distribution in the plume of a solid rocket motor (SRM). The use of an off-axis parabolic mirror in the experimental setup could suppress the jitter of light passing through the SRM plume, and the particle size in the plume of the measured SRM was in the order of microns. Full article
(This article belongs to the Special Issue Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion)
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23 pages, 9723 KiB  
Article
Assessment of the Thermodynamic and Numerical Modeling of LES of Multi-Component Jet Mixing at High Pressure
by Alexander Begemann, Theresa Trummler, Alexander Doehring, Michael Pfitzner and Markus Klein
Energies 2023, 16(5), 2113; https://doi.org/10.3390/en16052113 - 22 Feb 2023
Cited by 1 | Viewed by 1707
Abstract
Mixing under high pressure conditions plays a central role in several engineering applications, such as direct-injection engines and liquid rocket engines. Numerical flow simulations have become a complementary tool to study the mixing process under these conditions but require complex thermodynamic modeling as [...] Read more.
Mixing under high pressure conditions plays a central role in several engineering applications, such as direct-injection engines and liquid rocket engines. Numerical flow simulations have become a complementary tool to study the mixing process under these conditions but require complex thermodynamic modeling as well as validation with accurate experimental data. For this reason, we use experiments of supercritical single-phase jet mixing from the literature, where the mixing is quantified by the mixture speed of sound, as a reference for our work. We here focus on the thermodynamic modeling of multi-component flows under high pressure conditions and the analytical calculation of the mixture speed of sound. Our thermodynamic model is based on cubic equations of state extended for multi-components. Using an extension of OpenFOAM, we perform large-eddy simulations of hexane and pentane injections and compare our results with the experimentally measured mixture speed of sound at specific positions. The simulation results show the same characteristic trends, indicating that the mixing effects are well reproduced in the simulations. Additionally, the effect of the sub-grid scale modeling is assessed by comparing results using different models (Smagorinsky, Vreman, and Wall-Adapting Local Eddy-viscosity). The comprehensive simulation data presented here, in combination with the experimental data, provide a benchmark for numerical simulations of jet mixing in high pressure conditions. Full article
(This article belongs to the Special Issue Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion)
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16 pages, 5736 KiB  
Article
Numerical Study of Wall Heat Transfer Effects on Flow Separation in a Supersonic Overexpanded Nozzle
by Priyadharshini Murugesan, A. R. Srikrishnan, Akram Mohammad and Ratna Kishore Velamati
Energies 2023, 16(4), 1762; https://doi.org/10.3390/en16041762 - 10 Feb 2023
Viewed by 1863
Abstract
In this study, numerical simulations have been carried out to analyze the effect of convective heat transfer on flow separation occurring in a DLP-PAR nozzle. Heat transfer coefficient (0, 200 and 1000 w/m2K) was applied to the nozzle wall to incorporate [...] Read more.
In this study, numerical simulations have been carried out to analyze the effect of convective heat transfer on flow separation occurring in a DLP-PAR nozzle. Heat transfer coefficient (0, 200 and 1000 w/m2K) was applied to the nozzle wall to incorporate the cooling effect for different gas inlet temperatures ranging from 1000 to 1500 K. The impact of the cooling effect was analyzed based on nozzle wall temperature and wall static pressure. The wall static pressure distribution also characterizes movement of the separation point. For an inlet temperature of 1000 K, a detailed heat transfer study was carried out for four different nozzle pressure ratios (14, 22, 30 and 40). Significant amount of heat transfer was observed for pressure ratio 14, which in turn had an impact on flow separation. The wall cooling resulted in a shift of the point of separation towards the nozzle exit. For the nozzle pressure ratio of 14, this shift was by about 8.8%, indicating that the flow separation can be delayed by way of cooling for the considered inlet temperature. For higher inlet temperatures, the effect of heat transfer on flow separation seems to be negligible. The current study concludes that the separation point can be controlled by convective cooling for inlet gas temperatures below 1500 K so that the optimal performance of the nozzle can be achieved. Full article
(This article belongs to the Special Issue Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion)
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16 pages, 4530 KiB  
Article
Experimental Investigations on Detonation Initiation Characteristics of a Liquid-Fueled Pulse Detonation Combustor at Different Inlet Air Temperatures
by Wenhao Tan, Longxi Zheng, Jie Lu, Lingyi Wang and Daoen Zhou
Energies 2022, 15(23), 9102; https://doi.org/10.3390/en15239102 - 1 Dec 2022
Cited by 4 | Viewed by 1271
Abstract
The detonation initiation characteristics of a single tube liquid-fueled pulse detonation combustor (PDC) is investigated at different inlet air temperatures in this paper. The inner diameter of the PDC is 62 mm. Gasoline and air are used as fuel and oxidant, respectively. The [...] Read more.
The detonation initiation characteristics of a single tube liquid-fueled pulse detonation combustor (PDC) is investigated at different inlet air temperatures in this paper. The inner diameter of the PDC is 62 mm. Gasoline and air are used as fuel and oxidant, respectively. The inlet air temperature is 288–523 K and the operating frequency of the PDC is 10~30 Hz. The experimental results show that the deflagration to detonation transition (DDT) distance, detonation initiation time, DDT time and jet ignition time decrease with the increasing operating frequency at the same inlet temperature. When the inlet temperature is 288 K, the DDT distance is shortened from 860.5 mm to 787.7 mm as the operating frequency increases from 10 Hz to 30 Hz. The detonation initiation time, the jet ignition time and the DDT time are reduced from 10.01 ms, 7.66 ms and 2.35 ms to 6.55 ms, 4.99 ms and 1.56 ms, respectively. When the inlet air temperature increases, the atomization and evaporation of the gasoline is improved, which also leads to the decrease in the DDT distance, the detonation initiation time, the jet ignition time and the DDT time. For example, when the inlet air temperature increases from 288 K to 523 K at the frequency of 10 Hz, the DDT distance is shortened from 860.5 mm to 747.2 mm and the detonation initiation time, the jet ignition time and the DDT time is reduced to 5.867 ms, 2.51 ms and 1.11 ms, respectively. Additionally, the self-ignition caused by high inner wall temperature occurs when PDC is operating at high frequency under high inlet air temperature. Full article
(This article belongs to the Special Issue Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion)
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16 pages, 7005 KiB  
Article
Effect of Water Injection on Turbine Inlet under Different Flight Conditions
by Jiamao Luo, Shengfang Huang, Shunhua Yang, Wanzhou Zhang and Zhongqiang Mu
Energies 2022, 15(19), 7447; https://doi.org/10.3390/en15197447 - 10 Oct 2022
Cited by 1 | Viewed by 2247
Abstract
Numerical simulations were conducted to research the pre-cooling effects of water injection on the turbine inlet of a turbine-based combined cycle (TBCC) engine under different flight conditions. Then, the performance of the water injection pre-compressor cooling (WIPCC) engine was calculated by mathematical modelling [...] Read more.
Numerical simulations were conducted to research the pre-cooling effects of water injection on the turbine inlet of a turbine-based combined cycle (TBCC) engine under different flight conditions. Then, the performance of the water injection pre-compressor cooling (WIPCC) engine was calculated by mathematical modelling with different water to air ratios (WAR). It was the first time that the mass injection field of the turbine inlet of a TBCC engine was simulated, and it was also the first time that the performance of a subcomponent turbine engine of a TBCC was assessed. The calculation results showed the relationship of the inlet temperature with respect to WAR, inlet length and flight Mach number. The strategy for inlet length and water mass flow was proposed in order to meet the requirements of pre-cooling. When the length of the turbine inlet was 10 times the diameter of the inlet exit, the air could be cooled by 167.5 K with WAR = 0.09. The highest evaporation ratio reached at 93%. Finally, the calculation results revealed the performance of the water-pre-cooled turbine engine, of which the flight envelope was expanded to Ma3.0 from Ma2.3 by pre-cooling. The engine thrust as well as the specific impulse were significantly improved. The thrust reached at 0.9 times the characteristic thrust meeting the TBCC mode transition requirement of thrust and working speed spectrum. Full article
(This article belongs to the Special Issue Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion)
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Review

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40 pages, 5593 KiB  
Review
Cryogenic Hydrogen Jet and Flame for Clean Energy Applications: Progress and Challenges
by Jac Clarke, Wulf Dettmer, Jennifer Wen and Zhaoxin Ren
Energies 2023, 16(11), 4411; https://doi.org/10.3390/en16114411 - 30 May 2023
Cited by 3 | Viewed by 2489
Abstract
Industries across the world are making the transition to net-zero carbon emissions, as government policies and strategies are proposed to mitigate the impact of climate change on the planet. As a result, the use of hydrogen as an energy source is becoming an [...] Read more.
Industries across the world are making the transition to net-zero carbon emissions, as government policies and strategies are proposed to mitigate the impact of climate change on the planet. As a result, the use of hydrogen as an energy source is becoming an increasingly popular field of research, particularly in the aviation sector, where an alternative, green, renewable fuel to the traditional hydrocarbon fuels such as kerosene is essential. Hydrogen can be stored in multiple ways, including compressed gaseous hydrogen, cryo-compressed hydrogen and cryogenic liquid hydrogen. The infrastructure and storage of hydrogen will play a pivotal role in the realisation of large-scale conversion from traditional fuels, with safety being a key consideration. This paper provides a review on previous work undertaken to study the characterisation of both unignited and ignited hydrogen jets, which are fundamental phenomena for the utilisation of hydrogen. This includes work that focuses on the near-field flow structure, dispersion in the far-field, ignition and flame characteristics with multi-physics. The safety considerations are also included. The theoretical models and computational fluid dynamics (CFD) multiphase and reactive flow approaches are discussed. Then, an overview of previous experimental work is provided, before focusing the review on the existing computational results, with comparison to experiments. Upon completion of this review, it is highlighted that the complex near-field physics and flow phenomena are areas lacking in research. The near-field flow properties and characteristics are of significant importance with respect to the ignition and combustion of hydrogen. Full article
(This article belongs to the Special Issue Heat and Thermal Fluid Flow for Advanced Aerospace Propulsion)
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