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Journal articles on the topic 'Detonation wave engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 February 2022

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1

Pandey, K. M., and Pinku Debnath. "Review on Recent Advances in Pulse Detonation Engines." Journal of Combustion 2016 (2016): 1–16. http://dx.doi.org/10.1155/2016/4193034.

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Pulse detonation engines (PDEs) are new exciting propulsion technologies for future propulsion applications. The operating cycles of PDE consist of fuel-air mixture, combustion, blowdown, and purging. The combustion process in pulse detonation engine is the most important phenomenon as it produces reliable and repeatable detonation waves. The detonation wave initiation in detonation tube in practical system is a combination of multistage combustion phenomena. Detonation combustion causes rapid burning of fuel-air mixture, which is a thousand times faster than deflagration mode of combustion pr

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2

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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3

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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4

Prisacariu, Vasile, Constantin Rotaru, Ionică Cîrciu, and Mihai Niculescu. "Numerical simulation and performances evaluation of the pulse detonation engine." MATEC Web of Conferences 234 (2018): 01001. http://dx.doi.org/10.1051/matecconf/201823401001.

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A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. The engine is pulsed because the mixture must be renewed in the combustor between each detonation wave. Theoretically, a PDE can operate from subsonic up to hypersonic flight speed. Pulsed detonation engines offer many advantages over conventional propulsion systems and are regarded as potential replacements for air breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long range transports, high-speed vehicles, space laun

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5

Jackson, S. I., and J. E. Shepherd. "Toroidal Imploding Detonation Wave Initiator for Pulse Detonation Engines." AIAA Journal 45, no. 1 (2007): 257–70. http://dx.doi.org/10.2514/1.24662.

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6

Hutchins, T. E., and M. Metghalchi. "Energy and Exergy Analyses of the Pulse Detonation Engine." Journal of Engineering for Gas Turbines and Power 125, no. 4 (2003): 1075–80. http://dx.doi.org/10.1115/1.1610015.

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Energy and exergy analyses have been performed on a pulse detonation engine. A pulse detonation engine is a promising new engine, which uses a detonation wave instead of a deflagration wave for the combustion process. The high-speed supersonic combustion wave reduces overall combustion duration resulting in an nearly constant volume energy release process compared to the constant pressure process of gas turbine engines. Gas mixture in a pulse detonation engine has been modeled to execute the Humphrey cycle. The cycle includes four processes: isentropic compression, constant volume combustion,

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7

Ebrahimi, Houshang B., and Charles L. Merkle. "Wave Reverberations in Multitube Pulse Detonation Engines." Journal of Propulsion and Power 24, no. 2 (2008): 345–52. http://dx.doi.org/10.2514/1.32162.

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8

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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9

Valorani, M., M. Di Giacinto, and C. Buongiorno. "Performance prediction for oblique detonation wave engines (odwe)." Acta Astronautica 48, no. 4 (2001): 211–28. http://dx.doi.org/10.1016/s0094-5765(00)00161-2.

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10

KASAHARA, Jiro, Takakage ARAI, Kouki TAKAZAWA, and Akiko MATSUO. "721 Research and Development of Detonation Wave Engines." Proceedings of Conference of Hokkaido Branch 2001.41 (2001): 270–71. http://dx.doi.org/10.1299/jsmehokkaido.2001.41.270.

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11

Pan, Jiaying, Lin Chen, Haiqiao Wei, Dengquan Feng, Sili Deng, and Gequn Shu. "On autoignition mode under variable thermodynamic state of internal combustion engines." International Journal of Engine Research 21, no. 5 (2018): 856–65. http://dx.doi.org/10.1177/1468087418796617.

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Autoignition modes under premixed combustion conditions are usually studied in constant-volume configurations. However, the autoignition events related to knocking combustion in spark-ignition engines do experience variable volumes in combustion chamber and ever-changing thermodynamic states caused by reciprocating piston motion and main flame front compression. Such combustion situations may lead to different autoignition modes from constant-volume scenarios. Using one-dimensional direct numerical simulations with detailed chemistry and transport of H2/air mixture, the autoignition modes duri

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12

Wang, Aifeng, Jiahao Shang, Qiu Wang, and Kuanliang Wang. "Effects of Cowl-Induced Expansion on the Wave Complex Induced by Oblique Detonation Wave Reflection." Processes 9, no. 7 (2021): 1215. http://dx.doi.org/10.3390/pr9071215.

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Oblique detonation wave (ODW) reflection on the upper wall leads to a sophisticated wave complex, whose stability is critical to the application of oblique detonation engines. The unstable wave complex characterized with a continuous moving Mach stem has been observed, but the corresponding re-stability adjusting method is still unclear so far. In this study, the cowl-induced expansion wave based on the model with an upper-side expansion wall is introduced, and the ODW dynamics have been analyzed using the reactive Euler equations with a two-step induction–reaction kinetic model. With the addi

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13

Liu, Yu, Baoguo Xiao, Lan Wang, and Chao Wang. "Numerical Study of Disturbance Resistance of Oblique Detonation Waves." International Journal of Aerospace Engineering 2020 (December 1, 2020): 1–9. http://dx.doi.org/10.1155/2020/8876637.

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The stability of oblique detonation waves (ODWs) is a fundamental problem, and resistance of ODWs against disturbances is crucial for oblique detonation engines in high-speed propulsion. In this work, numerical studies on ODW stability in disturbed flows are conducted using the two-dimensional reactive Euler equations with a two-step induction-reaction kinetic model. Two kinds of flow disturbances are, respectively, introduced into the steady flow field to assess ODW stability, including upstream transient high-pressure disturbance (UTHD) and downstream jet flow disturbance (DJFD) with differe

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14

Starikovskiy, Andrey, Nickolay Aleksandrov, and Aleksandr Rakitin. "Plasma-assisted ignition and deflagration-to-detonation transition." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 370, no. 1960 (2012): 740–73. http://dx.doi.org/10.1098/rsta.2011.0344.

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Non-equilibrium plasma demonstrates great potential to control ultra-lean, ultra-fast, low-temperature flames and to become an extremely promising technology for a wide range of applications, including aviation gas turbine engines, piston engines, RAMjets, SCRAMjets and detonation initiation for pulsed detonation engines. The analysis of discharge processes shows that the discharge energy can be deposited into the desired internal degrees of freedom of molecules when varying the reduced electric field, E / n , at which the discharge is maintained. The amount of deposited energy is controlled b

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15

Nalim, M. R., and D. E. Paxson. "A Numerical Investigation of Premixed Combustion in Wave Rotors." Journal of Engineering for Gas Turbines and Power 119, no. 3 (1997): 668–75. http://dx.doi.org/10.1115/1.2817036.

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Wave rotor cycles that utilize premixed combustion processes within the passages are examined numerically using a one-dimensional CFD-based simulation. Internal-combustion wave rotors are envisioned for use as pressure-gain combustors in gas turbine engines. The simulation methodology is described, including a presentation of the assumed governing equations for the flow and reaction in the channels, the numerical integration method used, and the modeling of external components such as recirculation ducts. A number of cycle simulations are then presented that illustrate both turbulent-deflagrat

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16

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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17

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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18

Wang, Zhang, Wang, Han, and Chen. "Numerical Simulation of Knock Combustion in a Downsizing Turbocharged Gasoline Direct Injection Engine." Applied Sciences 9, no. 19 (2019): 4133. http://dx.doi.org/10.3390/app9194133.

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Engine knock has become the prime barrier to significantly improve power density and efficiency of the engines. To further look into the essence of the abnormal combustion, this work studies the working processes of normal combustion and knock combustion under practical engine operating conditions using a three-dimensional computation fluid dynamics (CFD) fluid software CONVERGE (Version 2.3.0, Convergent Science, Inc., Madison, USA). The results show that the tumble in the cylinder is gradually formed with the increase of the valve lift, enhances in the compression stroke and finally is broke

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19

Zhong and Liu. "Numerical Analysis of End-Gas Autoignition and Pressure Oscillation in a Downsized SI Engine Using Large Eddy Simulation." Energies 12, no. 20 (2019): 3909. http://dx.doi.org/10.3390/en12203909.

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Knock and super-knock are abnormal combustion phenomena in engines, however, they are hard to study comprehensively through optical experimental methods due to their inherent destructive nature. In present work, the methodology of large eddy simulation (LES) coupled with G equations and a detailed mechanism of primary reference fuel (PRF) combustion is utilized to address the mechanisms of knock and super-knock phenomena in a downsized spark ignition gasoline engine. The knock and super-knock with pressure oscillation are qualitatively duplicated through present numerical models. As a result,

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20

Bulat, Pavel, Anzhelika Melnikova, Vladimir Upyrev, and Konstantin Volkov. "Refraction of Oblique Shock Wave on a Tangential Discontinuity." Fluids 6, no. 9 (2021): 301. http://dx.doi.org/10.3390/fluids6090301.

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The refraction of an oblique shock wave on a tangential discontinuity dividing two gas flows with different properties is considered. It is shown that its partial reflection occurs with the exception of the geometrical diffraction of an oblique shock. Another oblique shock, expansion wave or weak discontinuity that coincides with the Mach line can act as a reflected disturbance. This study focuses on the relationships that define the type of reflected discontinuity and its parameters. The domains of shock wave configurations with various types of reflected discontinuities, including characteri

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21

Karimi, Abdullah, and M. Razi Nalim. "Ignition by Hot Transient Jets in Confined Mixtures of Gaseous Fuels and Air." Journal of Combustion 2016 (2016): 1–13. http://dx.doi.org/10.1155/2016/9565839.

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Ignition of a combustible mixture by a transient jet of hot reactive gas is important for safety of mines, prechamber ignition in IC engines, detonation initiation, and novel constant-volume combustors. The present work is a numerical study of the hot jet ignition process in a long constant-volume combustor (CVC) that represents a wave rotor channel. The hot jet of combustion products from a prechamber is injected through a converging nozzle into the main CVC chamber containing a premixed fuel-air mixture. Combustion in a two-dimensional analogue of the CVC chamber is modeled using a global re

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22

Золотько, Олександр Євгенович, Олена Василівна Золотько, Олександра Валеріївна Сосновська, Олександр Сергійович Аксьонов та Ірина Сергіївна Савченко. "ОСОБЛИВОСТІ КОНСТРУКТИВНИХ СХЕМ ДВИГУНІВ З ІМПУЛЬСНИМИ ДЕТОНАЦІЙНИМИ КАМЕРАМИ". Aerospace technic and technology, № 2 (27 квітня 2020): 4–10. http://dx.doi.org/10.32620/aktt.2020.2.01.

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The pressure of the products of chemical reactions in the chamber of a rocket engine increases significantly if the rocket fuel components burn in the detonation mode. In this case, it can get to a simpler and more reliable expulsion propellant feed system instead of a turbopump feed system. The value of heat release power (MW / liter) of detonation engines is several orders of magnitude larger than that of aircraft and rocket engines operating in the Brighton cycle. The high rate of energy released in the detonation mode can significantly reduce the mass, the inertia, and overall dimensions o

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23

Bicalho Civinelli de Almeida, Victor, and Dieter Peitsch. "Aeroelastic assessment of a highly loaded high pressure compressor exposed to pressure gain combustion disturbances." Journal of the Global Power and Propulsion Society 2 (October 15, 2018): F72OUU. http://dx.doi.org/10.22261/jgpps.f72ouu.

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A numerical aeroelastic assessment of a highly loaded high pressure compressor exposed to flow disturbances is presented in this paper. The disturbances originate from novel, inherently unsteady, pressure gain combustion processes, such as pulse detonation, shockless explosion, wave rotor or piston topping composite cycles. All these arrangements promise to reduce substantially the specific fuel consumption of present-day aeronautical engines and stationary gas turbines. However, their unsteady behavior must be further investigated to ensure the thermodynamic efficiency gain is not hindered by

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24

Bradley, Derek. "Autoignitions and detonations in engines and ducts." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 370, no. 1960 (2012): 689–714. http://dx.doi.org/10.1098/rsta.2011.0367.

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The origins of autoignition at hot spots are analysed and the pressure pulses that arise from them are related to knock in gasoline engines and to developing detonations in ducts. In controlled autoignition engines, autoignition is benign with little knock. There are several modes of autoignition and the existence of an operational peninsula, within which detonations can develop at a hot spot, helps to explain the performance of various engines. Earlier studies by Urtiew and Oppenheim of the development of autoignitions and detonations ahead of a deflagration in ducts are interpreted further,

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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

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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27

Debnath, Pinku, and Krishna Murari Pandey. "Computational Study of Deflagration to Detonation Transition in Pulse Detonation Engine Using Shchelkin Spiral." Applied Mechanics and Materials 772 (July 2015): 136–40. http://dx.doi.org/10.4028/www.scientific.net/amm.772.136.

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Detonation combustion wave is much more energetic combustion process in pulse detonation engine combustion system. Numerous experimental, theoretical and numerical analyses have been studied in pulse detonation engine to implement in practical propulsion system. In this present computational study the simulation was carried out for deflagration flame acceleration and deflagration to detonation transition of hydrogen air combustible mixture inside the detonation tube with and without Shchelkin spiral. A three dimensional computational analysis has been done by finite volume discretization metho

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28

DOGRA, Bharat Ankur, Mehakveer SINGH, Tejinder Kumar JINDAL, and Subhash CHANDER. "Technological advancements in Pulse Detonation Engine Technology in the recent past: A Characterized Report." INCAS BULLETIN 11, no. 4 (2019): 81–92. http://dx.doi.org/10.13111/2066-8201.2019.11.4.8.

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Pulse Detonation Engine (PDE), is an emerging and promising propulsive technology all over the world in the past few decades. A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. Theoretically, a PDE can be operate from subsonic to hypersonic flight speeds. Pulsed detonation engines offer many advantages over conventional air-breathing engines and are regarded as potential replacements for air-breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long-range transportation, h

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29

Zhou, Siyin, Tianyi Shi, and Wansheng Nie. "Study of plasma-assisted detonation initiation by quasi-direct current discharge." International Journal of Spray and Combustion Dynamics 12 (January 2020): 175682771989446. http://dx.doi.org/10.1177/1756827719894464.

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To study the effects of quasi-direct current discharge plasma on the initiation of a pulse detonation engine at multiple locations, we proposed a double-zones quasi-direct current discharge plasma ignition scheme. Based on the establishment of the plasma-assisted detonation initiation model, the process of detonation wave formation in the mixture of hydrogen and air by single and double ignition zone were studied by numerical method. The wave structure, component evolution history, and Zeldovich–von Neumann–Döring curve after forming a stable detonation wave were all discussed. The simulation

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30

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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31

Gulzar, Mubashir, M. Talal Jameel, Sufyan Tariq, and Umair Khalid. "Geometric Modeling of the Frequency of an Acoustic Detonation Pressure Wave in a Standard Spark Ignition Engine." Applied Mechanics and Materials 392 (September 2013): 146–50. http://dx.doi.org/10.4028/www.scientific.net/amm.392.146.

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In an archetypal engine the detonation frequency is usually analyzed using an overly simplistic model, incorporating only the rudimentary parameters (modeling the combustion chamber as a right circular cylinder). The research work is to develop a broader state space geometric model to discern the detonation frequency in a standard Otto engine based on engine conformation parameters. The intent of this project is to model the detonation event using a broader state-space i.e.to build on Draper’s Acoustic Wave Pressure formula and develop a sound underlying mathematical structure manifesting the

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32

Ashford, S. A., and G. Emanuel. "Oblique detonation wave engine performance prediction." Journal of Propulsion and Power 12, no. 2 (1996): 322–27. http://dx.doi.org/10.2514/3.24031.

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33

Xiong, Cha, Hua Qiu, and Qinwei Lu. "The Ignition of Two Phase Detonation by a Branching Detonation Tube." International Journal of Turbo & Jet-Engines 34, no. 4 (2016): 387–93. http://dx.doi.org/10.1515/tjj-2016-0019.

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Abstract A branching tube is available to deliver sufficient energy to directly initiate a detonation wave. But sustaining the detonation wave through a branching tube is a challenge. In this study, a preliminary exploration about a branching pulsed detonation engine with a gas-liquid mixture was carried out to evaluate filling conditions on detonation initiation. Two detonation tubes were connected by three different schemes, such as Tail-Tail, Tail-Mid, and Tail-Head. Experimental results showed only end-head connected tubes can be ignited by the branching tube, which is quite different from

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34

Grigoriev, A. V., O. A. Rudakov, and A. V. Solovieva. "Gas dynamic calculation of detonation in variable cross-section ducts." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 1 (2019): 42–54. http://dx.doi.org/10.18287/2541-7533-2019-18-1-42-54.

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Formulas of gas dynamic calculation of detonation parameters in variable cross-section ducts are presented and a design detonation diagram is given. The diagram shows the detonation characteristics of super-compressed detonation and under-compressed detonation as the function of shock wave specific speed depending on the intensity of temperature of the ideal gas in a subsonic one-dimensional flow behind the shock wave propagating in a chemically active air-fuel mixture and on the ratio of geometrical expansion (convergence) of the duct. The propagation of a stationary shock-wave the static pre

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35

Vasil'ev, A. A. "The Principal Aspects of Application of Detonation in Propulsion Systems." Journal of Combustion 2013 (2013): 1–15. http://dx.doi.org/10.1155/2013/945161.

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The basic problems of application of detonation process in propulsion systems with impulse and continuous burning of combustible mixture are discussed. The results on propagation of detonation waves in supersonic flow are analyzed relatively to air-breathing engine. The experimental results are presented showing the basic possibility of creation of an engine with exterior detonation burning. The base results on optimization of initiation in impulse detonation engine are explained at the expense of spatial and temporal redistribution of an energy, entered into a mixture. The method and techniqu

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36

Srikrishnan, S., P. K. Dash, and V. Jayakumar. "Evaluation of critical blockage ratio and pulse length in a pulse detonation engine using CFD and MATLAB." MATEC Web of Conferences 172 (2018): 02006. http://dx.doi.org/10.1051/matecconf/201817202006.

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A Pulse Detonation Engine (PDE) is a new invented propulsion device that takes advantage of the pressure rise inherent to the efficient burning of fuel-air mixtures via detonations. Detonation initiation is a critical process that occurs in the cycle of a PDE. A practical method of detonation initiation is Deflagration-to-Detonation Transition (DDT), which describes the acceleration of a subsonic deflagration created using low initiation energies to a supersonic detonation. The DDT process is not well understood due to a wide range of time and length scales involving complex chemistry, turbule

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37

Asogan, K., and Jamuna Venkatesan. "Theoretical Investigation on Combustion with Preformed Vortex Patterns." Applied Mechanics and Materials 812 (November 2015): 44–50. http://dx.doi.org/10.4028/www.scientific.net/amm.812.44.

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The formation of swirl to improve mixing in the fuel-air mixture through induced turbulence, by making changes in the combustion chamber geometry has been the key interest mentioned in the published research, academic and commercial works. The occurrence of shock waves has long been the effect of engine detonation. Both these things involve variation in the fluid’s dynamic characteristics, thermodynamic and physical states that are controllable by the use of mechanically produced waves. This paper aims at exploring the ways by which optimal combustion can be achieved through wave assisted comb

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38

Bennewitz, John W., Blaine R. Bigler, Mathias C. Ross, Stephen A. Danczyk, William A. Hargus, and Richard D. Smith. "Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths." Energies 14, no. 8 (2021): 2037. http://dx.doi.org/10.3390/en14082037.

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A rotating detonation rocket engine (RDRE) with various convergent nozzles and chamber lengths is investigated. Three hundred hot-fire tests are performed using methane and oxygen ranging from equivalence ratio equaling 0.5–2.5 and total propellant flow up to 0.680 kg/s. For the full-length (76.2 mm) chamber study, three nozzles at contraction ratios ϵc = 1.23, 1.62 and 2.40 are tested. Detonation is exhibited for each geometry at equivalent conditions, with only fuel-rich operability slightly increased for the ϵc = 1.62 and 2.40 nozzles. Despite this, counter-propagation, i.e., opposing wave

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39

Xu, Gui-yang, Chun-guang Wang, Shao-qing Hu, Jian-Liang Gong, and Zhe Deng. "Investigation on the Time Error of Detonation Acoustic in Process of Formation and Propagation." International Journal of Turbo & Jet-Engines 36, no. 4 (2019): 391–99. http://dx.doi.org/10.1515/tjj-2018-0011.

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Abstract The time error of detonation acoustic in process of detonation formation and propagation in a multi-cycle gas-liquid two-phase pulsed detonation engine is experimentally investigated. Results from the tests show that before the detonation wave escapes through the open-end of PDE tube, the maximum average arrival time error of detonation acoustic is achieved in the process of overdriven detonation. After detonation wave exists of PDE tube, arrival time error at 0 deg is greater than the other directivity angles in all distances and increases dramatically first and then almost stays at

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Nalim, M. R., Z. A. Izzy, and P. Akbari. "Rotary wave-ejector enhanced pulse detonation engine." Shock Waves 22, no. 1 (2011): 23–38. http://dx.doi.org/10.1007/s00193-011-0348-5.

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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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Ma, Hu, Zhenjuan Xia, Wei Gao, Changfei Zhuo, and Dong Wang. "Numerical simulation of the deflagration-to-detonation transition of iso-octane vapor in an obstacle-filled tube." International Journal of Spray and Combustion Dynamics 10, no. 3 (2018): 244–59. http://dx.doi.org/10.1177/1756827718758047.

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Flame acceleration and deflagration-to-detonation transition of an iso-octane vapor–air mixture in an obstacle-filled detonation tube were simulated by solving Navier–Stokes equations with a single-step reaction mechanism. A variable specific heat ratio was used in these simulations. Detonation cell size was successfully simulated for the iso-octane vapor–air mixture. Two methods for initiating detonation waves were revealed in a detonation tube with obstacles. Pressure and flame parameters, such as the temporal variation of total energy release rate, flame front location, propagation velocity

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Vasyliv, S. S., and H. O. Strelnykov. "Rocket engine thrust vector control by detonation product injection into the supersonic portion of the nozzle." Technical mechanics 2020, no. 4 (2020): 29–34. http://dx.doi.org/10.15407/itm2020.04.029.

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For solving non-traditional problems of rocket flight control, in particular, for the conditions of impact of a nuclear explosion, non-traditional approaches to the organization of the thrust vector control of a rocket engine are required. Various schemes of gas-dynamic thrust vector control systems that counteract impact actions on the rocket were studied. It was found that the dynamic characteristics of traditional gas-dynamic thrust vector control systems do not allow one to solve the problem of counteracting impact actions on the rocket. Appropriate dynamic characteristics can provide a pe

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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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Cambier, Jean-Luc, Henry Adelman, and Gene P. Menees. "Numerical simulations of an oblique detonation wave engine." Journal of Propulsion and Power 6, no. 3 (1990): 315–23. http://dx.doi.org/10.2514/3.25436.

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Nalim, M. R. "Assessment of Combustion Modes for Internal Combustion Wave Rotors." Journal of Engineering for Gas Turbines and Power 121, no. 2 (1999): 265–71. http://dx.doi.org/10.1115/1.2817116.

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Combustion within the channels of a wave rotor is examined as a means of obtaining pressure gain during heat addition in a gas turbine engine. Three modes of combustion are assessed: premixed autoignition (detonation), premixed deflagration, and non-premixed autoignition. The last two will require strong turbulence for completion of combustion in a reasonable time in the wave rotor. The autoignition modes will require inlet temperatures in excess of 800 K for reliable ignition with most hydrocarbon fuels. Examples of combustion mode selection are presented for two engine applications.

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Li, Jian-ling, Wei Fan, Hua Qiu, Chuan-jun Yan, and Yu-Qian Wang. "Preliminary study of a pulse normal detonation wave engine." Aerospace Science and Technology 14, no. 3 (2010): 161–67. http://dx.doi.org/10.1016/j.ast.2009.12.002.

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Grigoriev, A. V., O. A. Rudakov, and A. V. Solovieva. "Gas dynamic calculation of detonation in constant-cross-section ducts." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 3 (2019): 48–58. http://dx.doi.org/10.18287/2541-7533-2019-18-3-48-58.

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The paper presents a computational method with the use of gas-dynamic functions of parameters of detonation in a one-dimensional subsonic flow of ideal gas behind the shock wave propagating in chemically active air-and-fuel mixture in a uniform-cross-section duct, where the resultant of normal pressure forces acting on its side surface is equal to zero. Stabilization of the shock wave is provided by the onset of thermal crisis with the air-and-fuel mixture combustion heat supply to the gas behind the wave. In this case the value of the specific speed of the combustion products is equal to the

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Yao, Songbai, Meng Liu, and Jianping Wang. "Numerical Investigation of Spontaneous Formation of Multiple Detonation Wave Fronts in Rotating Detonation Engine." Combustion Science and Technology 187, no. 12 (2015): 1867–78. http://dx.doi.org/10.1080/00102202.2015.1067202.

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Azatian, V. V., G. K. Vedeshkin, and Yu M. Filatov. "Chemical methods to control combustion, explosion and gas detonation." Вестник Российской академии наук 89, no. 3 (2019): 279–84. http://dx.doi.org/10.31857/s0869-5873893279-284.

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The identification of the chain reactions of gas combustion at atmospheric and elevated pressures has created not only new features of combustion theory, but also wide opportunities for the effective management of the processes of combustion, explosion, and detonation. This can be improved by controlling the rates of multiplication and destruction of active intermediate particles: free atoms and radicals, using inhibitors and promoters. This article briefly describes the use of methods developed to prevent the ignition and explosion of methane in the air: including in coal mines; the ignition

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