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Journal articles on the topic 'Rotating detonation engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 January 2023

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1

Wang, Yuhui, Wenyou Qiao, and JialingLe. "Combustion Characteristics in Rotating Detonation Engines." International Journal of Aerospace Engineering 2021 (March 13, 2021): 1–17. http://dx.doi.org/10.1155/2021/8839967.

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A lot of studies on rotating detonation engines have been carried out due to the higher thermal efficiency. However, the number, rotating directions, and intensities of rotating detonation waves are changeful when the flow rate, equivalence ratio, inflow conditions, and engine schemes vary. The present experimental results showed that the combustion mode of a rotating detonation engine was influenced by the combustor scheme. The annular detonation channel had an outer diameter of 100 mm and an inner diameter of 80 mm. Air and hydrogen were injected into the combustor from 60 cylindrical orific

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2

Xie, Qiaofeng, Zifei Ji, Haocheng Wen, Zhaoxin Ren, Piotr Wolanski, and Bing Wang. "Review on the Rotating Detonation Engine and It’s Typical Problems." Transactions on Aerospace Research 2020, no. 4 (2020): 107–63. http://dx.doi.org/10.2478/tar-2020-0024.

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Abstract Detonation is a promising combustion mode to improve engine performance, increase combustion efficiency, reduce emissions, and enhance thermal cycle efficiency. Over the last decade, significant progress has been made towards the applications of detonation mode in engines, such as standing detonation engine (SDE), Pulse detonation engine (PDE) and rotating detonation engine (RDE), and the understanding of the fundamental chemistry and physics processes in detonation engines via experimental and numerical studies. This article is to provide a comprehensive overview of the progress in t

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3

Ji, Zifei, Ruize Duan, Renshuai Zhang, Huiqiang Zhang, and Bing Wang. "Comprehensive Performance Analysis for the Rotating Detonation-Based Turboshaft Engine." International Journal of Aerospace Engineering 2020 (July 2, 2020): 1–11. http://dx.doi.org/10.1155/2020/9587813.

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The potential advantages of rotating detonation combustion are gradually approved, and it is becoming a stable and controllable energy conversion way adopted to the propulsion devices or ground-engines. This study focuses on the rotating detonation-based turboshaft engine, and the architecture is presented for this form of engine with compatibility between the turbomachinery and rotating detonation combustor being realized. The parametric performance simulation model for the rotating detonation-based turboshaft engine are developed. Further, the potential performance benefits as well as their

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4

Sosa, Jonathan, Kareem A. Ahmed, Robert Fievisohn, John Hoke, Timothy Ombrello, and Frederick Schauer. "Supersonic driven detonation dynamics for rotating detonation engines." International Journal of Hydrogen Energy 44, no. 14 (2019): 7596–606. http://dx.doi.org/10.1016/j.ijhydene.2019.02.019.

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5

Wang, Yu Hui, and Jian Ping Wang. "Rotating Detonation Instabilities in Hydrogen-Oxygen Mixture." Applied Mechanics and Materials 709 (December 2014): 56–62. http://dx.doi.org/10.4028/www.scientific.net/amm.709.56.

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Rotating detonation engines are studied more and more widely because of high thermodynamic efficiency and high specific impulse. Rotating detonation of hydrogen and oxygen was achieved in this study. Rotating detonation waves were observed by high speed cameras and detonation pressure traces were recorded by PCB pressure sensors. The velocity of rotating detonation waves is fluctuating during the run. Low frequency detonation instabilities, intermediate frequency detonation instabilities and high frequency detonation instabilities were discovered. They are relevant to unsteady heat release, ac

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6

Zhou, Jianping, Feilong Song, Shida Xu, Xingkui Yang, and Yongjun Zheng. "Investigation of Rotating Detonation Fueled by Liquid Kerosene." Energies 15, no. 12 (2022): 4483. http://dx.doi.org/10.3390/en15124483.

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The performance of rotating detonation engines (RDEs) is theoretically better than that of traditional aero engines because of self-pressurization. A type of swirl injection scheme is introduced in this paper for two-phase detonation. On the one hand, experiments are performed on continuous rotating detonation of ternary “kerosene, hydrogen and oxygen-enriched air” mixture in an annular combustor. It is found that increasing the mass fraction of hydrogen can boost the wave speed and the stability of detonation waves’ propagation. One the other hand, characteristics of kerosene–hot air RDE is i

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7

Zhou, Rui, Dan Wu, and Jianping Wang. "Progress of continuously rotating detonation engines." Chinese Journal of Aeronautics 29, no. 1 (2016): 15–29. http://dx.doi.org/10.1016/j.cja.2015.12.006.

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8

Wang, Yuhui, and Jianping Wang. "Coexistence of detonation with deflagration in rotating detonation engines." International Journal of Hydrogen Energy 41, no. 32 (2016): 14302–9. http://dx.doi.org/10.1016/j.ijhydene.2016.06.026.

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9

Batista, Armani, Mathias C. Ross, Christopher Lietz, and William A. Hargus. "Descending Modal Transition Dynamics in a Large Eddy Simulation of a Rotating Detonation Rocket Engine." Energies 14, no. 12 (2021): 3387. http://dx.doi.org/10.3390/en14123387.

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Rotating detonation rocket engines (RDREs) exhibit various unsteady phenomena, including modal transitions, that significantly affect their operation, performance and stability. The dynamics of the detonation waves are studied during a descending modal transition (DMT) where four co-rotating detonations waves decrease to three in a gaseous methane-oxygen RDRE. Detonation wave tracking is applied to capture, visualize and analyze unsteady, 3D detonation wave dynamics data within the combustion chamber of the RDRE. The mechanism of a descending modal transition is the failure of a detonation wav

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10

Frolov, Sergey M., Igor O. Shamshin, Viktor S. Aksenov, Vladislav S. Ivanov, and Pavel A. Vlasov. "Ion Sensors for Pulsed and Continuous Detonation Combustors." Chemosensors 11, no. 1 (2023): 33. http://dx.doi.org/10.3390/chemosensors11010033.

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Presented in the article are the design and operation principles of ion sensors intended for detecting the propagating reaction fronts, the deflagration/detonation mode, apparent subsonic/supersonic propagation velocity of the reaction front, and duration of heat release by measuring the ion current in the reactive medium. The electrical circuits for ion sensors without and with intermediate amplifiers, with short response time and high sensitivity, as well as with the very wide dynamic range of operation in the reactive media with highly variable temperature and pressure, are provided and dis

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11

Bennewitz, John W., Blaine R. Bigler, Jessica J. Pilgram, and William A. Hargus. "MODAL TRANSITIONS IN ROTATING DETONATION ROCKET ENGINES." International Journal of Energetic Materials and Chemical Propulsion 18, no. 2 (2019): 91–109. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.2019027880.

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12

Koch, James, and J. Nathan Kutz. "Modeling thermodynamic trends of rotating detonation engines." Physics of Fluids 32, no. 12 (2020): 126102. http://dx.doi.org/10.1063/5.0023972.

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13

Yan, Chenglong, Wei Lin, Chen Shu, Yue Zhi, and Wei He. "Numerical study of air-breathing two-phase rotating detonation engine under Ma 6 flight conditions." Journal of Physics: Conference Series 2364, no. 1 (2022): 012063. http://dx.doi.org/10.1088/1742-6596/2364/1/012063.

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Abstract Air-breathing two-phase rotating detonation engines possess high thermodynamic cycle efficiency and have attracted extensive attention in domain of wide range flight aircraft. In this study, an engine configuration is proposed, and the corresponding numerical model is established using the Euler-Lagrange method. The engine type is suitable for flying at an altitude of 28 kilometers and a flying speed of Ma 6. Our data show that the engine operates primarily in chaos in this flight state. The peak pressure of the detonation wave is about 0.85 MPa, the peak temperature of the detonation

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14

Xiong, Dapeng, Mingbo Sun, Haoyang Peng, et al. "Numerical Investigation of Contact Burning in an Air-Breathing Continuous Rotating Detonation Engine." International Journal of Aerospace Engineering 2022 (March 19, 2022): 1–13. http://dx.doi.org/10.1155/2022/1487613.

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Three-dimensional (3D) numerical simulations of a continuous rotating detonation engine are carried out with an unsteady Reynolds-averaged Navier-Stokes solver. The second-order upwind advection upstream splitting method and second-order Runge-Kutta method are used to discretize space and time terms, and detailed 9-species 19-step hydrogen-oxygen reactions are applied in this study. Nonpremixed rotating detonation is successfully realized numerically, and the characteristics of the detonation wave are revealed. The expanding angle of the combustor has a great impact on the shape of the detonat

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15

Heister, Stephen D., John Smallwood, Alexis Harroun, Kevin Dille, Ariana Martinez, and Nathan Ballintyn. "Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines." Aerospace 9, no. 10 (2022): 581. http://dx.doi.org/10.3390/aerospace9100581.

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Rotating (also termed continuous spin) detonation technology is gaining interest in the global research and development community due to the potential for increased performance. Potential performance benefits, thrust chamber design, and thrust chamber cooling loads are analyzed for propellant applications using liquid oxygen or high-concentration hydrogen peroxide oxidizers with kerosene, hydrogen, and methane fuels. Performance results based on a lumped parameter treatment show that theoretical specific impulse gains of 3–14% are achievable with the highest benefit coming from hydrogen-fueled

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16

Langston, Lee S. "Detonation Gas Turbines." Mechanical Engineering 135, no. 12 (2013): 50–54. http://dx.doi.org/10.1115/1.2013-dec-4.

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This article focuses on various technical and functional aspects of detonation gas turbines. Detonation combustion involves a supersonic flow, with the chemical reaction front accelerating, driving a shock wave system in its advancement. In the 1990s, detonation-based power concepts began with pulse detonation engines (PDEs), and have now moved into the continuous detonation mode, termed rotating detonation engines (RDEs). Modern gas turbine combustors are compact, robust, tolerant of a wide variety of fuels, and provide the highest combustion intensities. The single-spool RDE gas turbine is r

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17

Mikhalchenko, E. V., V. F. Nikitin, Yu G. Phylippov, and L. I. Stamov. "Numerical study of rotating detonation onset in engines." Shock Waves 31, no. 7 (2021): 763–76. http://dx.doi.org/10.1007/s00193-021-01051-5.

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18

Wang, Yuhui, and Jialing Le. "Rotating detonation engines with two fuel orifice schemes." Acta Astronautica 161 (August 2019): 262–75. http://dx.doi.org/10.1016/j.actaastro.2019.05.035.

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19

Nordeen, Craig A., and Lee S. Langston. "There's a New Cycle in Town." Mechanical Engineering 140, no. 07 (2018): 36–41. http://dx.doi.org/10.1115/1.2018-jul-2.

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The promises of increased efficiency, simplicity, and high power density are driving the current research focus on rotating detonation engines (RDEs). An engine that uses detonation rather than deflagration could have some key advantages. If harnessed in a gas turbine or rocket, detonation could reduce the need for some expensive hardware, lighten engine weight and increase power output and efficiency. Today, variants of the RDE as a combustor for gas turbines, rockets, and scramjets are being explored at the Air Force Research Laboratory (AFRL), Naval Research Laboratory, Naval Postgraduate S

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20

Wolański, P. "RDE research and development in Poland." Shock Waves 31, no. 7 (2021): 623–36. http://dx.doi.org/10.1007/s00193-021-01038-2.

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AbstractA very short survey of research conducted in Poland on the development of the rotating detonation engine (RDE) is presented. Initial studies conducted in cooperation with Japanese partners lead to development of a joint patent on RDE. Then, an intensive basic and applied research was started at the Institute of Heat Engineering of the Warsaw University of Technology. One of the first achievements was the demonstration of performance of the rocket engine with an aerospike nozzle utilizing continuously rotating detonation (CRD), and research was directed into development of a small turbo

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21

Wang, Yuhui, and Jialing Le. "Experimental study of sharp noise caused by rotating detonation waves." Noise Control Engineering Journal 70, no. 6 (2022): 527–39. http://dx.doi.org/10.3397/1/377046.

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Previous studies of rotating detonation engines (RDEs) focused on combustion, heat transfer, and propulsion, but not noise, which is considered here. High-frequency pressure sensors, such as dynamic sensors, are often used as contact measurements to determine the detonation pressure and rotating detonation cycle time, but they obtain data for only a few seconds. Here, a simple and inexpensive acoustic measurement method is used to obtain the high-frequency sound pressure of the detonation and cycle time over more than a few hours and is not affected by high-temperature products. The results sh

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22

Prisacariu, Vasile, Constantin Rotaru, and Mihai Leonida Niculescu. "Considerations and simulations about Pulse Detonation Engine." MATEC Web of Conferences 290 (2019): 04009. http://dx.doi.org/10.1051/matecconf/201929004009.

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PDE propulsion can work from a subsonic regime to hypersonic regimes; this type of engine can have higher thermodynamic efficiency compared to other turbojet or turbofan engines due to the removal of rotating construction elements (compressors and turbines) that can reduce the mass and total cost of propulsion system. The PDE experimental researches focused on both the geometric configuration and the thermo-gas-dynamic flow aspects to prevent uncontrolled self-ignition. This article presents a series of numerical simulations on the functioning of PDE with hydrogen at supersonic regimens.

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23

Schwer, Douglas, and Kailas Kailasanath. "Numerical investigation of the physics of rotating-detonation-engines." Proceedings of the Combustion Institute 33, no. 2 (2011): 2195–202. http://dx.doi.org/10.1016/j.proci.2010.07.050.

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24

Wu, Dan, Rui Zhou, Meng Liu, and Jianping Wang. "Numerical Investigation of the Stability of Rotating Detonation Engines." Combustion Science and Technology 186, no. 10-11 (2014): 1699–715. http://dx.doi.org/10.1080/00102202.2014.935641.

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25

Yan, Chenglong, Chen Shu, Jiafeng Zhao, et al. "Influences of thermal physical property parameters on operating characteristics of simulated rotating detonation ramjet fueled by C₁₂H₂₃." AIP Advances 12, no. 11 (2022): 115309. http://dx.doi.org/10.1063/5.0101939.

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Two-phase rotating detonation ramjets are considered to be suitable for aerospace applications due to their high thermodynamic cycle efficiency. These engines have an extremely complex internal flow field, in which the liquid fuel undergoes physical and chemical processes such as fragmentation, evaporation, mixing, and combustion; these processes also interact with detonation waves that have significant gradients. This makes it difficult to simulate a three-dimensional (3D) full-process rotating detonation combustion chamber. Here, based on the Euler–Lagrangian simulation method, a 3D numerica

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26

Smith, Richard D., and Steven B. Stanley. "Experimental Investigation of Rotating Detonation Rocket Engines for Space Propulsion." Journal of Propulsion and Power 37, no. 3 (2021): 463–73. http://dx.doi.org/10.2514/1.b37959.

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27

Braun, James, Bayindir H. Saracoglu, and Guillermo Paniagua. "Unsteady Performance of Rotating Detonation Engines with Different Exhaust Nozzles." Journal of Propulsion and Power 33, no. 1 (2017): 121–30. http://dx.doi.org/10.2514/1.b36164.

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28

Mizener, Andrew R., Frank K. Lu, and Patrick E. Rodi. "Performance Sensitivities of Rotating Detonation Engines Installed onto Waverider Forebodies." Journal of Propulsion and Power 35, no. 2 (2019): 289–302. http://dx.doi.org/10.2514/1.b37033.

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29

Wang, Fang, and Chunsheng Weng. "Numerical research on two-phase kerosene/air rotating detonation engines." Acta Astronautica 192 (March 2022): 199–209. http://dx.doi.org/10.1016/j.actaastro.2021.12.026.

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30

Liu, M., R. Zhou, and J. P. Wang. "Numerical Investigation of Different Injection Patterns in Rotating Detonation Engines." Combustion Science and Technology 187, no. 3 (2014): 343–61. http://dx.doi.org/10.1080/00102202.2014.923411.

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31

Kindracki, Jan, Krzysztof Wacko, Przemysław Woźniak, Stanisław Siatkowski, and Łukasz Mężyk. "Influence of Gaseous Hydrogen Addition on Initiation of Rotating Detonation in Liquid Fuel–Air Mixtures." Energies 13, no. 19 (2020): 5101. http://dx.doi.org/10.3390/en13195101.

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Hydrogen is the most common molecule in the universe. It is an excellent fuel for thermal engines: piston, turbojet, rocket, and, going forward, in thermonuclear power plants. Hydrogen is currently used across a range of industrial applications including propulsion systems, e.g., cars and rockets. One obstacle to expanding hydrogen use, especially in the transportation sector, is its low density. This paper explores hydrogen as an addition to liquid fuel in the detonation chamber to generate thermal energy for potential use in transportation and generation of electrical energy. Experiments wit

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32

Fotia, Matthew L., John Hoke, and Fred Schauer. "Experimental Performance Scaling of Rotating Detonation Engines Operated on Gaseous Fuels." Journal of Propulsion and Power 33, no. 5 (2017): 1187–96. http://dx.doi.org/10.2514/1.b36213.

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33

Liu, Yan, Weijiang Zhou, Yunjun Yang, Zhou Liu, and Jianping Wang. "Numerical study on the instabilities in H2-air rotating detonation engines." Physics of Fluids 30, no. 4 (2018): 046106. http://dx.doi.org/10.1063/1.5024867.

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34

Schwer, Douglas, and K. Kailasanath. "Fluid dynamics of rotating detonation engines with hydrogen and hydrocarbon fuels." Proceedings of the Combustion Institute 34, no. 2 (2013): 1991–98. http://dx.doi.org/10.1016/j.proci.2012.05.046.

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35

Wu, Dan, Yan Liu, Yusi Liu, and Jianping Wang. "Numerical investigations of the restabilization of hydrogen–air rotating detonation engines." International Journal of Hydrogen Energy 39, no. 28 (2014): 15803–9. http://dx.doi.org/10.1016/j.ijhydene.2014.07.159.

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36

Harroun, Alexis J., Stephen D. Heister, and Joseph H. Ruf. "Computational and Experimental Study of Nozzle Performance for Rotating Detonation Rocket Engines." Journal of Propulsion and Power 37, no. 5 (2021): 660–73. http://dx.doi.org/10.2514/1.b38244.

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37

Yao, Song-Bai, Meng Liu, and Jian-Ping Wang. "The Effect of the Inlet Total Pressure and the Number of Detonation Waves on Rotating Detonation Engines." Procedia Engineering 99 (2015): 848–52. http://dx.doi.org/10.1016/j.proeng.2014.12.611.

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38

Luan, Zhenye, Yue Huang, Sijia Gao, and Yancheng You. "Formation of multiple detonation waves in rotating detonation engines with inhomogeneous methane/oxygen mixtures under different equivalence ratios." Combustion and Flame 241 (July 2022): 112091. http://dx.doi.org/10.1016/j.combustflame.2022.112091.

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39

Bedick, Clinton R., Charlotte Albunio, Peter Strakey, Donald Ferguson, and Rigel Woodside. "Potassium carbonate decomposition modeling within rotating detonation engines for direct power extraction applications." Combustion and Flame 244 (October 2022): 112263. http://dx.doi.org/10.1016/j.combustflame.2022.112263.

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40

Zhou, Rui, Dan Wu, Yan Liu, and Jian-Ping Wang. "Particle path tracking method in two- and three-dimensional continuously rotating detonation engines." Chinese Physics B 23, no. 12 (2014): 124704. http://dx.doi.org/10.1088/1674-1056/23/12/124704.

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41

Zhang, Li-Feng, John Z. Ma, Shu-Jie Zhang, Ming-Yi Luan, and Jian-Ping Wang. "Three-dimensional numerical study on rotating detonation engines using reactive Navier-Stokes equations." Aerospace Science and Technology 93 (October 2019): 105271. http://dx.doi.org/10.1016/j.ast.2019.07.004.

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42

Wang, Fang, Chunsheng Weng, Yuwen Wu, Qiaodong Bai, Quan Zheng, and Han Xu. "Numerical research on kerosene/air rotating detonation engines under different injection total temperatures." Aerospace Science and Technology 103 (August 2020): 105899. http://dx.doi.org/10.1016/j.ast.2020.105899.

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43

Wang, Fang, Huangwei Zhang, Qiaodong Bai, and Chunsheng Weng. "Numerical simulations of vapor kerosene/air rotating detonation engines with different slot inlet configurations." Acta Astronautica 194 (May 2022): 286–300. http://dx.doi.org/10.1016/j.actaastro.2022.02.015.

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44

Zhou, R., and J. P. Wang. "Numerical investigation of shock wave reflections near the head ends of rotating detonation engines." Shock Waves 23, no. 5 (2013): 461–72. http://dx.doi.org/10.1007/s00193-013-0440-0.

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45

Zhou, Rui, and Jian-Ping Wang. "Numerical investigation of flow particle paths and thermodynamic performance of continuously rotating detonation engines." Combustion and Flame 159, no. 12 (2012): 3632–45. http://dx.doi.org/10.1016/j.combustflame.2012.07.007.

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46

Zhu, Wenchao, and Yuhui Wang. "Effect of hydrogen flow rate and particle diameter on coal-hydrogen-air rotating detonation engines." International Journal of Hydrogen Energy 47, no. 2 (2022): 1328–42. http://dx.doi.org/10.1016/j.ijhydene.2021.10.088.

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47

Anand, Vijay, and Ephraim Gutmark. "A review of pollutants emissions in various pressure gain combustors." International Journal of Spray and Combustion Dynamics 11 (January 2019): 175682771987072. http://dx.doi.org/10.1177/1756827719870724.

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Recent years have witnessed a significant growth in the advancement and study of various unsteady combustors because of the prospective stagnation pressure gain offered by them. The pressure gain combustion produced by this class of combustors is poised to produce a step-change increase in the thermodynamic efficiency of gas-turbine engines. The current manuscript is oriented toward presenting a review on the pollutant emission characteristics of these devices; specifically, studies done so far on wave rotor combustors, pulsejet combustors, pulse detonation combustors, and rotating detonation

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48

Nejaamtheen, M. N., T. Y. Kim, P. K. Pavalavanni, J. Ryu, and J. Y. Choi. "Effects of the dimensionless radius of an annulus on the detonation propagation characteristics in circular and non-circular rotating detonation engines." Shock Waves 31, no. 7 (2021): 703–15. http://dx.doi.org/10.1007/s00193-021-01065-z.

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49

Wang, Y., J. Le, C. Wang, Y. Zheng, and S. Huang. "The effect of the throat width of plug nozzles on the combustion mode in rotating detonation engines." Shock Waves 29, no. 4 (2018): 471–85. http://dx.doi.org/10.1007/s00193-018-0865-6.

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50

Fureby, Christer, Guillaume Sahut, Alessandro Ercole, and Thommie Nilsson. "Large Eddy Simulation of Combustion for High-Speed Airbreathing Engines." Aerospace 9, no. 12 (2022): 785. http://dx.doi.org/10.3390/aerospace9120785.

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Large Eddy Simulation (LES) has rapidly developed into a powerful computational methodology for fluid dynamic studies, between Reynolds-Averaged Navier–Stokes (RANS) and Direct Numerical Simulation (DNS) in both accuracy and cost. High-speed combustion applications, such as ramjets, scramjets, dual-mode ramjets, and rotating detonation engines, are promising propulsion systems, but also challenging to analyze and develop. In this paper, the building blocks needed to perform LES of high-speed combustion are reviewed. Modelling of the unresolved, subgrid terms in the filtered LES equations is hi

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