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Aerospace
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Advances in Hypersonic Aircraft Propulsion Technology
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Advances in Hypersonic Aircraft Propulsion Technology

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 July 2023) | Viewed by 12232

Special Issue Editor

Dr. Qingchun Yang

E-Mail Website
Guest Editor
School of Astronautics, Beihang University, Beijing 100191, China
Interests: scramjet engine; aerospace combined cycle engine system; hypersonic propulsion technology; magnesium-fueled Martian ramjet engine; scramjet engines with nanoparticle-loaded hydrocarbon fuel; synergetic air-breathing rocket engine optimization; rotating detonation engine; supersonic combustion simulation and experiments; liquid jet breakup in supersonic crossflow; supercritical endothermic hydrocarbon fuel injection

Special Issue Information

Dear Colleagues,

Numerous experiments and studies performed over the past 50 years have shown the potential benefits of hypersonic aircraft. The revolutionary method of propulsion which makes this possible is the scramjet engine and high-performance propulsion systems, such as turbine-based combined cycle (TBCC) or rocket-based combined cycle (RBCC) systems. Overall, propulsion technology is developing toward the goals of large thrust, high speed, and long endurance, for both civil aircrafts and defense applications.

Heat transfer and flow dynamics are the main topics of concern for propulsion systems. Thermal protection has become the biggest problem for aircraft operating at hypersonic speeds due to external aerodynamic heating and internal combustion heat. In addition to more research on thermal management, research into advanced spray, combustion, and flow control technology is also necessary to ensure high combustion efficiency in advanced propulsion systems. Novel or optimized computational and experimental methods can be applied to measure spray, combustion, heat transfer, and flow dynamics within propulsion systems.

This Special Issue aims to provide an overview of recent advances in hypersonic aircraft propulsion technology. Authors are invited to submit full research articles and review manuscripts addressing (but not limited to) the following topics:

  • Overall design of hypersonic aircrafts;
  • Scramjets;
  • Combined cycle engine;
  • Precooled combined cycle engine;
  • Magnesium fueled Martian ramjet engine;
  • Detonation engine;
  • Integrated subsystem design;
  • Aerothermodynamic characterization of high-speed vehicles;
  • Air-breathing propulsion systems;
  • Space launch applications;
  • Supersonic combustion modelling and simulation;
  • Laser-based combustion diagnostics
  • Spray jet in supersonic crossflow;
  • Power fuel fluidization and combustion technology;
  • Impact of sustainable aviation fuels: biofuels, liquid hydrogen, etc.;
  • Endothermic hydrocarbon fuel, energetic hydrocarbon fuel, and nanoparticle-loaded hydrocarbon fuel;
  • Structural analysis and multidisciplinary multiobjective optimization;
  • Supercritical fluid flow and heat transfer;
  • Internal and external cooling of turbine blades;
  • Nanofluid heat transfer;
  • Thermal protection of structures;
  • Aerodynamics of engine components.

Dr. Qingchun Yang
Guest Editor

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

  • hypersonic aircrafts
  • scramjets
  • combined cycle engine
  • detonation engine
  • air-breathing propulsion systems
  • supersonic combustion
  • spray dynamics
  • supercritical fluid
  • sustainable aviation fuel
  • thermal protection of structures

Published Papers (7 papers)

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Research

22 pages, 14209 KiB  
Communication
Maximum-Thrust Nozzle Based on Height Constraints
by Bowen Huang, Jinglei Xu and Kaikai Yu
Aerospace 2023, 10(12), 976; https://doi.org/10.3390/aerospace10120976 - 21 Nov 2023
Viewed by 881
Abstract
Compared to conventional aircraft, hypersonic aircraft place a greater emphasis on the integration of aircraft and engines to meet their high-performance requirements. The design challenges of the nozzle are evident in the requirement of a significant area ratio between the inlet and outlet, [...] Read more.
Compared to conventional aircraft, hypersonic aircraft place a greater emphasis on the integration of aircraft and engines to meet their high-performance requirements. The design challenges of the nozzle are evident in the requirement of a significant area ratio between the inlet and outlet, as well as the need for the aircraft to have a compact overall size. In this study, the height constraint is directly incorporated into the maximum-thrust nozzle design method. A new method is proposed for designing nozzles under height constraints, taking into consideration the maximum thrust theory. Initially, a mathematical deduction of the condition in which the nozzle achieves the maximum thrust under the height constraint is performed. The method of characteristics is then used to develop a nozzle design that satisfies the height constraint. Subsequently, the influence of the design parameters on the design method is studied in a parametric manner. The results show that the Mach number scale and asymmetrical factors can affect the length of the nozzle’s ramp and flap, respectively. These factors greatly influence the performance of axial thrust and lift within a specific height constraint. Compared to the traditional truncation design method, the proposed method increases the thrust coefficient by 11.93% and the lift by 138.45%. Full article
(This article belongs to the Special Issue Advances in Hypersonic Aircraft Propulsion Technology)
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22 pages, 11172 KiB  
Article
Large Eddy Simulation and Dynamic Mode Decomposition of Supersonic Combustion Instability in a Strut-Based Scramjet Combustor
by Yuwei Cheng, Qian Chen, Xiaofei Niu and Shufeng Cai
Aerospace 2023, 10(10), 857; https://doi.org/10.3390/aerospace10100857 - 29 Sep 2023
Cited by 1 | Viewed by 866
Abstract
Supersonic combustion instability studies are crucial for the future maturation of scramjet engines. In the present paper, the supersonic combustion instability in a strut-based scramjet combustor is investigated through large eddy simulation and dynamic mode decomposition. The results show significant pressure oscillation in [...] Read more.
Supersonic combustion instability studies are crucial for the future maturation of scramjet engines. In the present paper, the supersonic combustion instability in a strut-based scramjet combustor is investigated through large eddy simulation and dynamic mode decomposition. The results show significant pressure oscillation in the strut-based scramjet combustor when the air parameters at the combustor inlet and the fuel parameters at the injector outlet are under certain conditions, and these pressure oscillation situations correspond to supersonic combustion instability. The oscillations have multiple dominant frequencies, including relatively low frequency of 2984 Hz, high frequency of 62,180 Hz, and very high frequency of 110,562 Hz. Large pressure oscillations in the strut-based scramjet combustor are closely related to wake instability, shear layer instability, shear layer and wave interactions, and combustion. Reducing the air total temperature at the combustor inlet can attenuate the pressure oscillations, and reducing the fuel flow rate at the injector outlet can also attenuate the pressure oscillations. Full article
(This article belongs to the Special Issue Advances in Hypersonic Aircraft Propulsion Technology)
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18 pages, 3063 KiB  
Article
Optimization Design of the NUAA-PTRE: A New Pre-Cooled Turbine Engine Adapting to 0~5 Mach Number
by Zhaohui Yao, Yuanzhao Guo, Jun Niu, Zhiguang Jin, Tianhao Yu, Baojun Guo, Wenhao Pu, Xin Wei, Feng Jin, Bo Li and Mengying Liu
Aerospace 2023, 10(2), 185; https://doi.org/10.3390/aerospace10020185 - 15 Feb 2023
Cited by 2 | Viewed by 1519
Abstract
A model of a NUAA-PTRE pre-cooled air turbine engine was established. The design point parameters of the engine were optimized, including the pressure ratio, air flow rate of the compressor, efficiency, throat area, and efficiency of the turbine. The air flow rate at [...] Read more.
A model of a NUAA-PTRE pre-cooled air turbine engine was established. The design point parameters of the engine were optimized, including the pressure ratio, air flow rate of the compressor, efficiency, throat area, and efficiency of the turbine. The air flow rate at the engine operating point was 142.73 kg/s. High performance of the key components under a wide range of working conditions was realized after optimization. To achieve the indicators of the overall scheme, adaptability studies of key components were conducted. A three-stage variable geometry design was applied to the inlet. The pre-cooler was optimized with a power-to-weight ratio of over 100 kW/kg and a compactness of 278 m2/m3. The built-in rocket gas generator and dual-component injector were developed, and the combustion and heat transfer processes were simulated. The overall optimization design of the NUAA-PTRE and the adaptive design of the components were completed, and high performance of the engine in a wide range of flight conditions at Ma 0~5 and altitude 0~25 km was achieved. Full article
(This article belongs to the Special Issue Advances in Hypersonic Aircraft Propulsion Technology)
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11 pages, 3721 KiB  
Article
Supersonic Combustion Mode Analysis of a Cavity Based Scramjet
by Yu Meng, Wenming Sun, Hongbin Gu, Fang Chen and Ruixu Zhou
Aerospace 2022, 9(12), 826; https://doi.org/10.3390/aerospace9120826 - 15 Dec 2022
Cited by 4 | Viewed by 1703
Abstract
Since flame stability is the key to the performance of scramjets, scramjet combustion mode and instability characteristics were investigated by using the POD method based on a cavity-stabilized scramjet. Experiments were developed on a directly connected scramjet model that had an inlet flow [...] Read more.
Since flame stability is the key to the performance of scramjets, scramjet combustion mode and instability characteristics were investigated by using the POD method based on a cavity-stabilized scramjet. Experiments were developed on a directly connected scramjet model that had an inlet flow of Mach 2.5 with a cavity stabilizer. CH* chemiluminescence, schlieren, and a wall static pressure sensor were employed to observe flow and combustion behavior. Three typical combustion modes were classified by distinguishing averaged CH* chemiluminescence images of three ethylene fuel jet equivalence ratios. The formation reason was explained using schlieren images and pressure characteristics. POD modes (PDMs) were determined using the proper orthogonal decomposition (POD) of sequential flame CH* chemiluminescence images. The PSD (power spectral density) of the PDM spectra showed large peaks in a frequency range of 100–600 Hz for three typical stabilized combustion modes. The results provide oscillation characteristics of three scramjet combustion modes. Full article
(This article belongs to the Special Issue Advances in Hypersonic Aircraft Propulsion Technology)
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13 pages, 5157 KiB  
Article
A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System
by Jun Liu, Huacheng Yuan, Jinsheng Zhang and Zheng Kuang
Aerospace 2022, 9(11), 685; https://doi.org/10.3390/aerospace9110685 - 03 Nov 2022
Cited by 2 | Viewed by 1274
Abstract
As hypersonic vehicles are highly integrated, a multifidelity simulation method based on a commercial solver is developed to reduce simulation time for such vehicles and their propulsion systems. This method is characterized by high-level fidelity numerical analysis of external flow and low-level fidelity [...] Read more.
As hypersonic vehicles are highly integrated, a multifidelity simulation method based on a commercial solver is developed to reduce simulation time for such vehicles and their propulsion systems. This method is characterized by high-level fidelity numerical analysis of external flow and low-level fidelity numerical analysis of internal flow. The external flow of a propulsion system is solved by RANS equations. The internal flow is modeled by a quasi-one-dimensional equation. The interaction between external and internal flow is governed by a CFD solver through a user-defined function (UDF). The static pressure distribution acquired from the multifidelity simulation method is in agreement with the experimental data, indicating that this simulation method can be used to study the flow physics of hypersonic propulsion systems at a reasonable cost. From a design perspective, the results indicate that the horizontal force increases with the fuel equivalence ratio, and the thrust balance is realized at φ = 0.35. The positive net thrust is maintained throughout the flight regime from Ma 4 to Ma 7, whether the combustor operates in ramjet or scramjet mode. Full article
(This article belongs to the Special Issue Advances in Hypersonic Aircraft Propulsion Technology)
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20 pages, 8031 KiB  
Article
Experimental and Numerical Investigations on the Mixing Process of Supercritical Jet Injected into a Supersonic Crossflow
by Wenyuan Zhou, Kai Xing, Suyi Dou, Qingchun Yang and Xu Xu
Aerospace 2022, 9(11), 631; https://doi.org/10.3390/aerospace9110631 - 22 Oct 2022
Cited by 4 | Viewed by 1551
Abstract
The mixing process and distribution characteristics of a supercritical endothermic hydrocarbon fuel (EHF) jet injected into a supersonic crossflow were investigated by experimental and numerical methods, respectively. The schlieren system and acetone planar laser-induced fluorescence (PLIF) optical system were used to capture the [...] Read more.
The mixing process and distribution characteristics of a supercritical endothermic hydrocarbon fuel (EHF) jet injected into a supersonic crossflow were investigated by experimental and numerical methods, respectively. The schlieren system and acetone planar laser-induced fluorescence (PLIF) optical system were used to capture the flow-field structural characteristics and instantaneous plume. The mixture and real gas models were employed to calculate the interaction of a transverse jet and supersonic crossflow and reveal a good accuracy with the experimental results. The mixing efficiency and total pressure loss were analyzed based on the numerical results. The results indicate that the supercritical-state EHF directly changes to a gaseous state as it enters the supersonic crossflow from the injector. The EHF jet plume boundary increases with the increasing momentum flux ratio (q). As the streamwise and spanwise distance increases, the traverse heights and expand width increase, and the EHF jet plume presents a semicircle shape in the cross-sectional plane. With the increase in the traverse direction, the concentration distribution shows a fast and then slow power exponential decreasing law; the highest concentration point starts from the near-wall region and rises in the transverse direction with the flow distance increasing. For the same injection condition, the higher the inflow Mach number, the higher the mixing efficiency. For the same Ma, the mixing efficiency is better for the case with low injection pressure and high injection temperature. The total pressure loss is greater in the higher Ma, and high injection pressure conditions cause greater total pressure loss. Full article
(This article belongs to the Special Issue Advances in Hypersonic Aircraft Propulsion Technology)
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13 pages, 1948 KiB  
Article
Flight/Propulsion Integrated Control of Over-Under TBCC Engine Based on GA-LQR Method
by Huafeng Yu, Yingqing Guo, Xinghui Yan and Jiamei Wang
Aerospace 2022, 9(10), 621; https://doi.org/10.3390/aerospace9100621 - 19 Oct 2022
Cited by 3 | Viewed by 1810
Abstract
Turbine-based combined cycle (TBCC) engines are one of the ideal powers for reusable air-breathing supersonic aircraft, but the flight/propulsion integrated control and mode transition restricts its use. This paper takes the Mach 4 over-under TBCC engine as the research object. The inlet is [...] Read more.
Turbine-based combined cycle (TBCC) engines are one of the ideal powers for reusable air-breathing supersonic aircraft, but the flight/propulsion integrated control and mode transition restricts its use. This paper takes the Mach 4 over-under TBCC engine as the research object. The inlet is established by the quasi-one-dimensional calculation theory, which can reflect the shock wave position. An iterative method is proposed, which points out that the flow rate in the mode transition depends on the flow capacity. By connecting the input and output that affect each other, the simulation of the coupling characteristics of the aircraft and engine are realized. A GA-LQR-based controller design method is proposed and verified through the aircraft’s climb and mode transition conditions. The simulation shows that the integrated control system can ensure the stability of the aircraft and the safe operation of the engine in the above two situations. During the mode transition process, the aircraft altitude and Mach number fluctuate less than 1%, and the normal shock wave of inlet is in a safe position. Full article
(This article belongs to the Special Issue Advances in Hypersonic Aircraft Propulsion Technology)
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