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Journal articles on the topic 'Rotating Detonations'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 February 2022

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1

Zhang, Hailong, Weidong Liu, Lin Zhang, Shijie Liu, and Luxin Jiang. "Effects of Chamber Width on H2/Air Rotating Detonations." International Journal of Aerospace Engineering 2020 (October 20, 2020): 1–14. http://dx.doi.org/10.1155/2020/8819667.

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To get the effects of chamber width on the H2/Air rotating detonations, several models with different widths have been investigated. By using a one-step chemical reaction model, one wave is induced in all models. The chamber width has a significant effect on the flow field. When the chamber width is small, the variation of the flow field with the radius is not obvious. But when the width increases, the curvature of the detonation wave reflecting between the inner and outer walls at the head would become enlarged. The height of the detonation wave both on the inner wall and the outer wall has b

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2

Fink, M., M. Kromer, W. Hillebrandt, et al. "Thermonuclear explosions of rapidly differentially rotating white dwarfs: Candidates for superluminous Type Ia supernovae?" Astronomy & Astrophysics 618 (October 2018): A124. http://dx.doi.org/10.1051/0004-6361/201833475.

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The observed sub-class of “superluminous” Type Ia supernovae lacks a convincing theoretical explanation. If the emission of such objects were powered exclusively by radioactive decay of 56Ni formed in the explosion, a progenitor mass close to or even above the Chandrasekhar limit for a non-rotating white dwarf star would be required. Masses significantly exceeding this limit can be supported by differential rotation. We, therefore, explore explosions and predict observables for various scenarios resulting from differentially rotating carbon–oxygen white dwarfs close to their respective limit o

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3

Hishida, Manabu, Toshi Fujiwara, and Piotr Wolanski. "Fundamentals of rotating detonations." Shock Waves 19, no. 1 (2009): 1–10. http://dx.doi.org/10.1007/s00193-008-0178-2.

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4

Anand, Vijay, and Ephraim Gutmark. "Rotating Detonations and Spinning Detonations: Similarities and Differences." AIAA Journal 56, no. 5 (2018): 1717–22. http://dx.doi.org/10.2514/1.j056892.

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5

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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6

García-Senz, D., R. M. Cabezón, and I. Domínguez. "Surface and Core Detonations in Rotating White Dwarfs." Astrophysical Journal 862, no. 1 (2018): 27. http://dx.doi.org/10.3847/1538-4357/aacb7d.

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7

St. George, A., R. Driscoll, V. Anand, and E. Gutmark. "On the existence and multiplicity of rotating detonations." Proceedings of the Combustion Institute 36, no. 2 (2017): 2691–98. http://dx.doi.org/10.1016/j.proci.2016.06.132.

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8

Jodele, Justas, Vijay Anand, Alexander Zahn, Nathan Chiles, and Ephraim Gutmark. "Quantification of Rotating Detonations Using OH* Chemiluminescence at Varied Widths." AIAA Journal 59, no. 7 (2021): 2457–66. http://dx.doi.org/10.2514/1.j059737.

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9

Teng, Honghui, Lin Zhou, Pengfei Yang, and Zonglin Jiang. "Numerical investigation of wavelet features in rotating detonations with a two-step induction-reaction model." International Journal of Hydrogen Energy 45, no. 7 (2020): 4991–5001. http://dx.doi.org/10.1016/j.ijhydene.2019.12.063.

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10

Bildsten, Lars. "Explosions on a Variety of Scales." Proceedings of the International Astronomical Union 7, S285 (2011): 71. http://dx.doi.org/10.1017/s1743921312000257.

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SummaryThe theoretical community is beginning to appreciate (and predict) the potential diversity of explosive outcomes from stellar evolution, while the supernovæ surveys are finding new kinds of supernovæ. This talk described two such new supernovæ. The first are ultraluminous core collapse supernovæ with radiated energies approaching 1051 ergs. The talk went on to present our recent work that explains these events with late-time energy deposition from rapidly rotating, highly magnetized neutron stars: magnetars. It concluded with our theoretical work on helium shell detonations on accreting

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11

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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12

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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13

Vasil’ev, Anatoly A. "Rotating Detonation: History, Results, Problems." Transactions on Aerospace Research 2020, no. 4 (2020): 48–60. http://dx.doi.org/10.2478/tar-2020-0020.

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Abstract Among of modern papers devoted to numerical modeling of rotated waves the greater part of papers are based on assumption that such wave propagates with velocity equals to the Chapman-Jouguet velocity of ideal detonation model with plane front. But the experimental velocities of rotated detonation waves, as a rule, are less (and even much less) the velocity of ideal Chapman-Jouguet detonation. Such regimes are named as low-velocity detonation or quasi-detonation and its characteristics are practically not investigated carefully. Moreover, similar to the spinning detonation, the strong

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14

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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15

Wolański, Piotr. "Application of the Continuous Rotating Detonation to Gas Turbine." Applied Mechanics and Materials 782 (August 2015): 3–12. http://dx.doi.org/10.4028/www.scientific.net/amm.782.3.

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In this paper experimental research on rotating detonation carried out at the Institute of Aviation (IA) in Warsaw are presented. Research was focused on 3-D numerical simulations of detonation propagation in cylindrical chambers and on evaluation of conditions at which rotating detonation is propagating in cylindrical channels for kerosene-hydrogen-air mixtures. Conducted simulations are used for analysis of complex flow – detonation front interaction and for estimating the thermodynamic parameters of the outflow gases. Extensive research on continuously propagating rotating detonation in man

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16

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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17

Sun, Chengwen, Hongtao Zheng, Zhiming Li, Ningbo Zhao, Lei Qi, and Hongbo Guo. "Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor." Applied Sciences 9, no. 20 (2019): 4259. http://dx.doi.org/10.3390/app9204259.

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In this study, three-dimensional numerical studies have been performed to investigate the performance of a rotating detonation combustor with a diverging nozzle downstream. The effects of a diverging nozzle on the formation and propagation process of a detonation wave and typical flow field parameters in a rotating detonation combustor are mainly discussed. The results indicate that the diverging nozzle downstream is an important factor affecting the performance and design of a rotating detonation combustor. The diverging nozzle does not affect the formation and propagation process of the rota

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18

Yi, Tae-Hyeong, Jing Lou, Cary Kenny Turangan, and Piotr Wolanski. "Numerical Study of Detonation Processes in Rotating Detonation Engine and its Propulsive Performance." Transactions on Aerospace Research 2020, no. 3 (2020): 30–48. http://dx.doi.org/10.2478/tar-2020-0015.

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AbstractNumerical studies on detonation wave propagation in rotating detonation engine and its propulsive performance with one- and multi-step chemistries of a hydrogen-based mixture are presented. The computational codes were developed based on the three-dimensional Euler equations coupled with source terms that incorporate high-temperature chemical reactions. The governing equations were discretized using Roe scheme-based finite volume method for spatial terms and second-order Runge-Kutta method for temporal terms. One-dimensional detonation simulations with one- and multi-step chemistries o

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19

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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20

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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21

Anand, Vijay, Andrew St. George, Robert Driscoll, and Ephraim Gutmark. "Longitudinal pulsed detonation instability in a rotating detonation combustor." Experimental Thermal and Fluid Science 77 (October 2016): 212–25. http://dx.doi.org/10.1016/j.expthermflusci.2016.04.025.

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22

Qi, Lei, Zhitao Wang, Ningbo Zhao, Yongqiang Dai, Hongtao Zheng, and Qingyang Meng. "Investigation of the Pressure Gain Characteristics and Cycle Performance in Gas Turbines Based on Interstage Bleeding Rotating Detonation Combustion." Entropy 21, no. 3 (2019): 265. http://dx.doi.org/10.3390/e21030265.

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To further improve the cycle performance of gas turbines, a gas turbine cycle model based on interstage bleeding rotating detonation combustion was established using methane as fuel. Combined with a series of two-dimensional numerical simulations of a rotating detonation combustor (RDC) and calculations of cycle parameters, the pressure gain characteristics and cycle performance were investigated at different compressor pressure ratios in the study. The results showed that pressure gain characteristic of interstage bleeding RDC contributed to an obvious performance improvement in the rotating

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23

Ye-Tao, Shao, and Wang Jian-Ping. "Change in Continuous Detonation Wave Propagation Mode from Rotating Detonation to Standing Detonation." Chinese Physics Letters 27, no. 3 (2010): 034705. http://dx.doi.org/10.1088/0256-307x/27/3/034705.

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24

Fujii, Jumpei, Yoshiki Kumazawa, Akiko Matsuo, Soma Nakagami, Ken Matsuoka, and Jiro Kasahara. "Numerical investigation on detonation velocity in rotating detonation engine chamber." Proceedings of the Combustion Institute 36, no. 2 (2017): 2665–72. http://dx.doi.org/10.1016/j.proci.2016.06.155.

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25

Han, Hyung-Seok, Eun Sung Lee, and Jeong-Yeol Choi. "Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C2H4/O2 Propellant." Energies 14, no. 5 (2021): 1381. http://dx.doi.org/10.3390/en14051381.

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A small rotating detonation engine (RDE) model and the corresponding experimental setup were constructed for the experimental investigation of the detonation propagation characteristics and thrust performance of a circular RDE. Experiments were conducted at a range of 0.3–2.5 equivalence ratio with a total mass flow rate of less than 180.0 g/s using a C2H4/O2 mixture. Irregularly unstable detonative combustion occurs immediately after the detonation initiation, which includes initiation, propagation, decaying, and the merging of detonation waves. Following this, periodically unsteady detonativ

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26

Okninski, Adam, Jan Kindracki, and Piotr Wolanski. "Rocket rotating detonation engine flight demonstrator." Aircraft Engineering and Aerospace Technology 88, no. 4 (2016): 480–91. http://dx.doi.org/10.1108/aeat-07-2014-0106.

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27

Levin, V. A., I. S. Manuĭlovich, and V. V. Markov. "Formation of detonation in rotating channels." Doklady Physics 55, no. 6 (2010): 308–11. http://dx.doi.org/10.1134/s1028335810060145.

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28

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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29

Kawasaki, Akira, Tomoya Inakawa, Jiro Kasahara, et al. "Critical condition of inner cylinder radius for sustaining rotating detonation waves in rotating detonation engine thruster." Proceedings of the Combustion Institute 37, no. 3 (2019): 3461–69. http://dx.doi.org/10.1016/j.proci.2018.07.070.

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30

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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31

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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32

Hayashi, A. Koichi, Nobuyuki Tsuboi, and Edyta Dzieminska. "Numerical Study on JP-10/Air Detonation and Rotating Detonation Engine." AIAA Journal 58, no. 12 (2020): 5078–94. http://dx.doi.org/10.2514/1.j058167.

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33

Sato, Takuma, and Venkat Raman. "Detonation Structure in Ethylene/Air-Based Non-Premixed Rotating Detonation Engine." Journal of Propulsion and Power 36, no. 5 (2020): 752–62. http://dx.doi.org/10.2514/1.b37664.

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34

Wang, Zhan Lei, Yi Fan Li, Qun Mei, and Hui Ping Wang. "The Study on Detonation Front Shape of a Charge Shot by High-Speed Photography." Applied Mechanics and Materials 275-277 (January 2013): 697–701. http://dx.doi.org/10.4028/www.scientific.net/amm.275-277.697.

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In order to obtain the detonation front shape and spreading process of detonation wave, Rotating mirror multi-streak technique was used to shoot the detonation process of charge initiated from three points by high-speed photography technique. The record negative was read and these data were analyzed. The time differences of zero-time points and t-y coordinate curve were educed, and the chart of detonation wave shape was drew. The result provides a gist for warhead design. A method for analyzing and studying wave shape is offered.

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35

Yokoo, Ryuya, Keisuke Goto, Juhoe Kim, et al. "Propulsion Performance of Cylindrical Rotating Detonation Engine." AIAA Journal 58, no. 12 (2020): 5107–16. http://dx.doi.org/10.2514/1.j058322.

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36

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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37

Uemura, Yuho, A. Koichi Hayashi, Makoto Asahara, Nobuyuki Tsuboi, and Eisuke Yamada. "Transverse wave generation mechanism in rotating detonation." Proceedings of the Combustion Institute 34, no. 2 (2013): 1981–89. http://dx.doi.org/10.1016/j.proci.2012.06.184.

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38

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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39

Nordeen, C. A., D. Schwer, F. Schauer, J. Hoke, Th Barber, and B. Cetegen. "Thermodynamic model of a rotating detonation engine." Combustion, Explosion, and Shock Waves 50, no. 5 (2014): 568–77. http://dx.doi.org/10.1134/s0010508214050128.

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40

Levin, V. A., I. S. Manuylovich, and V. V. Markov. "Rotating Detonation Wave in an Annular Gap." Proceedings of the Steklov Institute of Mathematics 300, no. 1 (2018): 126–36. http://dx.doi.org/10.1134/s0081543818010108.

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41

Wang, Yuhui, and Jialing Le. "A hollow combustor that intensifies rotating detonation." Aerospace Science and Technology 85 (February 2019): 113–24. http://dx.doi.org/10.1016/j.ast.2018.12.014.

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42

Deng, Li, Hu Ma, Xiao Liu, and Changsheng Zhou. "Secondary shock wave in rotating detonation combustor." Aerospace Science and Technology 95 (December 2019): 105517. http://dx.doi.org/10.1016/j.ast.2019.105517.

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43

Bohon, Myles D., Richard Bluemner, C. Oliver Paschereit, and Ephraim J. Gutmark. "Measuring Rotating Detonation Combustion Using Cross-Correlation." Flow, Turbulence and Combustion 103, no. 1 (2019): 271–92. http://dx.doi.org/10.1007/s10494-019-00017-z.

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44

Braun, Eric M., Frank K. Lu, Donald R. Wilson, and José A. Camberos. "Airbreathing rotating detonation wave engine cycle analysis." Aerospace Science and Technology 27, no. 1 (2013): 201–8. http://dx.doi.org/10.1016/j.ast.2012.08.010.

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45

Mitura, K., M. Jedrzejewska-Szczerska, P. Ceynowa, et al. "Haemocompatibility Of Non-Functionalized And Plasmachemical Functionalized Detonation Nanodiamond Particles." Archives of Metallurgy and Materials 60, no. 3 (2015): 2183–89. http://dx.doi.org/10.1515/amm-2015-0364.

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AbstractThe purpose of this paper is to present the innovative design of microwave plasma system for modification of detonation nanodiamond particles (DNP) using a special rotating drum placed inside the reactor. Nanodiamond particles manufactured by detonation method reveal the biological activity depending on surface functionalization. Plasmachemical modification of detonation nanodiamond particles gives the possibility of controlling surface of nanodiamonds particles in biological tests. In this paper we would like to compare detonation nanodiamond (the grain sizes from 2 to 5 nm) with modi

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46

Prakash, Supraj, Romain Fiévet, Venkat Raman, Jason Burr, and Kenneth H. Yu. "Analysis of the Detonation Wave Structure in a Linearized Rotating Detonation Engine." AIAA Journal 58, no. 12 (2020): 5063–77. http://dx.doi.org/10.2514/1.j058156.

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47

Jin, Shan, Qingyang Meng, Zhiming Li, Ningbo Zhao, Hongtao Zheng, and Jialong Yang. "Numerical Investigation of Mixing Characteristic for CH4/Air in Rotating Detonation Combustor." Applied Sciences 10, no. 4 (2020): 1298. http://dx.doi.org/10.3390/app10041298.

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The mixing process of fuel and oxidizer is a very critical factor affecting the real operating performance of non-premixed rotating detonation combustor. In this paper, a two-dimensional numerical study is carried out to investigate the flow and mixing characteristics of CH4/air in combustor with different injection structures. On this basis, the effect of CH4/air mixing on the critical ignition energy for forming detonation is theoretically analyzed in detail. The numerical results indicate that injection strategies of CH4 and air can obviously affect the flow filed characteristic, pressure l

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48

Xia, Zhenjuan, Hu Ma, Changfei Zhuo, and Changsheng Zhou. "Propagation characteristics of rotating detonation wave in plane–radial structure with different pressure conditions." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 7 (2018): 2378–92. http://dx.doi.org/10.1177/0954410018779300.

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This paper simulates the propagation characteristics of rotating detonation wave in the plane–radial structure for mixtures of 2H2 + O2 + 3.76N2. Two-dimensional numerical simulation was modeled, and two kinds of typical flow field and corresponding operating range were obtained under various pressure conditions. Due to the influence of curvature, the detonation wave is strengthened near the outer concave boundary and weakened near the inner convex one. The pressure ratio was varied from 1.6 to 10 by varying both stagnation and back pressure for detonation parameters and flow parameters. It is

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49

Yan, Chian, Honghui Teng, and Hoi Dick Ng. "Effects of slot injection on detonation wavelet characteristics in a rotating detonation engine." Acta Astronautica 182 (May 2021): 274–85. http://dx.doi.org/10.1016/j.actaastro.2021.02.010.

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50

Neunteufel, P., S. C. Yoon, and N. Langer. "Evolution of helium star plus carbon-oxygen white dwarf binary systems and implications for diverse stellar transients and hypervelocity stars." Astronomy & Astrophysics 627 (June 25, 2019): A14. http://dx.doi.org/10.1051/0004-6361/201935322.

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Context. Helium accretion induced explosions in CO white dwarfs (WDs) are considered promising candidates for a number of observed types of stellar transients, including supernovae (SNe) of Type Ia and Type Iax. However, a clear favorite outcome has not yet emerged. Aims. We explore the conditions of helium ignition in the WD and the final fates of helium star-WD binaries as functions of their initial orbital periods and component masses. Methods. We computed 274 model binary systems with the Binary Evolution Code, in which both components are fully resolved. Both stellar and orbital evolution

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