Relevant bibliographies by topics / Detonation wave engines

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Detonation wave engines'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 February 2022

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Journal articles on the topic "Detonation wave engines"

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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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Detonation wave engines"

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Jouot, Fabien. "Etude de la détonation dans un jet diphasique cryogénique GH2-LOx : contribution aux études sur les moteurs à onde de détonation." Thesis, Orléans, 2009. http://www.theses.fr/2009ORLE2055/document.

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L’objectif de cette thèse est d’étudier l’initiation directe et la propagation d’une détonation dans un milieu cryogénique diphasique GH2-LOx dans le cadre général des moteurs à onde de détonation pour la propulsion spatiale. Un rappel des bases théoriques sur les processus d’atomisation d’un jet liquide, puis sur la détonation en phase gazeuse, et enfin sur la détonation dans un mélange diphasique, constituent le premier chapitre de la thèse. Le deuxième chapitre présente les dispositifs expérimentaux et les techniques utilisés pour mener à bien les expériences de caractérisation du jet dipha
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Medina, Carlos A. "Evaluation of straight and swept ramp obstacles on enhancing deflagration-to-detonation transition in pulse detonation engines." Thesis, Monterey, Calif. : Naval Postgraduate School, 2006. http://bosun.nps.edu/uhtbin/hyperion.exe/06Dec%5FMedina.pdf.

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Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, December 2006.<br>Thesis Advisor(s): Christopher M. Brophy. "December 2006." Includes bibliographical references (p. 107-108). Also available in print.
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Ess, Peter. "Numerical simulation of blunt-body generated detonation waves in viscous hypersonic ducted flows." Thesis, University of Bristol, 2003. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.288263.

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Rodriguez, Joel. "Investigation of transient plasma ignition for a Pulse Detonation Engine." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Mar%5FRodriguez.pdf.

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ALLGOOD, DANIEL CLAY. "AN EXPERIMENTAL AND COMPUTATIONAL STUDY OF PULSE DETONATION ENGINES." University of Cincinnati / OhioLINK, 2004. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1095259010.

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Wittmers, Nicole K. "Direct-connect performance evaluation of a valveless pulse detonation engine." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Dec%5FWittmers.pdf.

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Materano, Blanco Gilberto Ignacio. "Numerical modelling of pressure rise combustion for reducing emissions of future civil aircraft." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9259.

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This work assesses the feasibility of designing and implementing the wave rotor (WR), the pulse detonation engine (PDE) and the internal combustion wave rotor (ICWR) as part of novel Brayton cycles able to reduce emissions of future aircraft. The design and evaluation processes are performed using the simplified analytical solution of the devices as well as 1D-CFD models. A code based on the finite volume method is built to predict the position and dimensions of the slots for the WR and ICWR. The mass and momentum equations are coupled through a modified SIMPLE algorithm to model compressible
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Chan, Jimmy K. W. "Computational fluid dynamics analysis of shock propagation and reflection in a pulse detonation engine combustor." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Dec%5FChan%5FJimmy.pdf.

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Thesis (M.S. in Engineering Science (Mechanical))--Naval Postgraduate School, December 2003.<br>Thesis advisor(s): Chris M. Brophy, Garth V. Hobson. Includes bibliographical references (p. 103). Also available online.
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He, Hao. "Numerical simulations of unsteady flows in a pulse detonation engine by the conservation element and solution element method." Columbus, Ohio : Ohio State University, 2006. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1141850240.

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(6930197), Hasan Fatih Celebi. "Transient Response of Tapered and Angled Injectors Subjected to a Passing Detonation Wave." Thesis, 2019.

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A total number of 849 tests were conducted to investigate the transient response of liquid injectors with various geometries including different taper angles, injection angles and orifice lengths. High-speed videos were analyzed to characterize refill times and back-flow distances of nine different injector geometries subjected to a ethylene-oxygen detonation wave. Water was used as the working fluid and experiments were performed at two different vessel pressure settings (60 and 100 psia). Although a minimal difference was found between plain and angled injectors due to having constant orific
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Books on the topic "Detonation wave engines"

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Ostrander, M. J. Standing oblique detonation wave engine performance. AIAA, 1987.

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Lynch, E. D. Analysis of flow processes in the pulse detonation wave engine. American Institute of Aeronautics and Astronautics, 1994.

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O'Brien, C. J. Advanced earth-to-orbit propulsion concepts. AIAA, 1986.

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Cambier, Jean-Luc. Preliminary numerical simulations of a pulsed detonation wave engine. American Institute of Aeronautics and Astronautics, 1992.

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Roy, G. Advances in confined detonations. Torus Press, 2002.

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Skyring, R. Experimental determination of hydrogen-air detonation pressure limit and scramjet application. American Institute of Aeronautics and Astronautics, 1996.

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Fusina, Giovanni. Numerical investigation of oblique detonation waves for a shcramjet combustor. University of Toronto, Institute for Aerospace Studies, 2003.

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Oppitz, Rick. Aerothermodynamic performance of mixed compression, shock-induced combustion ramjets. University of Toronto, Institute for Aerospace Studies, 1995.

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Impulʹsnye detonat︠s︡ionnye dvigateli. Torus Press, 2006.

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G, Adelman Henry, Cambier Jean-Luc, and Ames Research Center, eds. Analytical and experimental investigations of the oblique detonation wave engine concept. National Aeronautics and Space Administration, Ames Research Center, 1991.

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Book chapters on the topic "Detonation wave engines"

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Bulat, Pavel, and Konstantin Volkov. "Laser Ignition for Pulse Detonation Engines." In Shock Wave Interactions. Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-73180-3_24.

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Fotia, Matthew L., John Hoke, and Frederick Schauer. "Performance of Rotating Detonation Engines for Air Breathing Applications." In Shock Wave and High Pressure Phenomena. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-68906-7_1.

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Liu, Xiang-Yang, Yan-Liang Chen, Song-Bai Yao, and Jian-Ping Wang. "Numerical Study of Reverse-Rotating Wave in the Hollow Rotating Detonation Engines." In Lecture Notes in Electrical Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_134.

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Wang, J. P., Y. F. Liu, and T. W. Li. "Numerical studies of pre-detonator ignition of pulse detonation engine." In Shock Waves. Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-27009-6_123.

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Vutthivithayarak, R., E. M. Braun, and F. K. Lu. "On Thermodynamic Cycles for Detonation Engines." In 28th International Symposium on Shock Waves. Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-25685-1_44.

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Li, J., Teo Chiang Juay, L. Li, P. H. Chang, and Boo-Cheong Khoo. "Criterion for Detonation Transition in Liquid-Fuel Pulse Detonation Engines." In 30th International Symposium on Shock Waves 1. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-46213-4_69.

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Wang, Jian-Ping, Song-Bai Yao, and Xu-Dong Han. "Continuous Detonation Engine Researches at Peking University." In Shock Wave and High Pressure Phenomena. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-68906-7_7.

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Mu, Q. H., C. Wang, W. Zhao, and Z. Jiang. "Experimental study on liquid-fueled pulse detonation engine." In Shock Waves. Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-27009-6_130.

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Kasahara, Jiro, Yuichi Kato, Kazuaki Ishihara, et al. "Application of Detonation Waves to Rocket Engine Chamber." In Shock Wave and High Pressure Phenomena. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-68906-7_4.

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Martyushov, S. N. "Numerical Simulation of Reactive Gas Mixes Flows in the Detonation Engine." In Shock Wave Interactions. Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-73180-3_25.

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Conference papers on the topic "Detonation wave engines"

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Sterling, J., K. Ghorbanian, J. Humphrey, T. Sobota, and D. Pratt. "Numerical investigations of pulse detonation wave engines." In 31st Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-2479.

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Akbari, Pezhman, and Razi Nalim. "Analysis of Flow Processes in Detonative Wave Rotors and Pulse Detonation Engines." In 44th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-1236.

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Wang, Bao, Hao He, and S.-T. John-Yu. "Direct Calculation of Wave Implosion for Detonation Initiation in Pulsed Detonation Engines." In 43rd AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-1306.

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Davidenko, Dmitry, Yohann Eude, Iskender Gokalp, and Francois Falempin. "Theoretical and Numerical Studies on Continuous Detonation Wave Engines." In 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2334.

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Saha, Pankaj, Pete Strakey, and Donald Ferguson. "Numerical Investigations of Instabilities in a Natural Gas-Air Fueled Rotating Detonation Engine." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91643.

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Abstract Recent numerical and experimental studies of Rotating Detonation Engines (RDEs) using air as the oxidizer have primarily focused on the ability to sustain a stable continuous detonation wave when fueled with hydrogen. For RDEs to be a viable technology for land-based power generation it is necessary to explore the ability to detonate natural gas and/or coal-syngas with air in the confines of the annular geometry of an RDE. There are major challenges in obtaining a stable detonation wave for a natural gas–air fueled RDE and to a lesser extent for coal-syngas and air. Recently published
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Bulat, P. V., N. B. Fedosenko, and V. V. Upyrev. "ON THE MECHANISM FOR MAINTAINING AN OVERDRIVEN DETONATION IN A ROTATING DETONATION ENGINE." In 8TH INTERNATIONAL SYMPOSIUM ON NONEQUILIBRIUM PROCESSES, PLASMA, COMBUSTION, AND ATMOSPHERIC PHENOMENA. TORUS PRESS, 2020. http://dx.doi.org/10.30826/nepcap2018-2-26.

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At present, virtually all jet engines are based on the Brighton thermodynamic cycle (combustion at constant pressure). The improvement of such engines has already reached its technological limit. A significant increase in the efficiency of jet engines (by 20%-25%) can be provided by a transition to the Fickett-Jacobs[4] thermodynamic cycle which uses detonation combustion. One possible realization is a rotating detonation engine (RDE) in which the combustion chamber is the space between two coaxial cylinders. In an ideal scheme, a fuel mixture is supplied from one end which is ignited by a sho
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Jackson, Scott, Martin Grunthaner, and Joseph Shepherd. "Wave Implosion as an Initiation Mechanism for Pulse Detonation Engines." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4820.

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Kailasanath, K. "Recent Developments in the Research on Rotating-Detonation-Wave Engines." In 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0784.

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Nageswara Reddy, Pereddy. "Performance Enhancement of Gas Turbine Engines Topped With Wave Rotors and Pulse Detonation Combustors." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14911.

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Abstract In the present research work, a novel method of integrating the conventional gas turbine engine with a Wave Rotor (WR) and a Pulse Detonation Combustor (PDC) is proposed to increase the specific work and thermal efficiency of the engine. Two gas turbine engine configurations, viz. (i) Baseline engine topped with a wave rotor and a steady flow combustor (BWRSFC), and (ii) Baseline engine topped with a wave rotor and a pulse detonation combustor (BWRPDC), have been analyzed with and without recuperative systems. In the case of BWRPDC, the principle of quasi-steady expansion of detonatio
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Jiang, Z. L., C. Wang, Z. M. Hu, and W. Zhao. "Numerical Analysis on Wave Dynamic Processes in Pulse Detonation Devices." In ASME 2002 Pressure Vessels and Piping Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/pvp2002-1580.

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In this paper, wave dynamics processes occurring in pulse detonation devices are analyzed both numerically and experimentally, including the propagation of detonation fronts, the motion of rarefaction waves in gas exhausting phase and the diffraction of shock waves at thrust nozzles. Numerical results are also compared with experiments to confirm the observed wave phenomena. In order to estimate operation roles of pulse detonation engines more accurately, the initiation of the air/hydrogen mixture is also examined experimentally at certain conditions. Numerical analysis indicates that pulse de
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Reports on the topic "Detonation wave engines"

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Costley, D., Luis De Jesús Díaz,, Sarah McComas, Christopher Simpson, James Johnson, and Mihan McKenna. Multi-objective source scaling experiment. Engineer Research and Development Center (U.S.), 2021. http://dx.doi.org/10.21079/11681/40824.

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The U.S. Army Engineer Research and Development Center (ERDC) performed an experiment at a site near Vicksburg, MS, during May 2014. Explosive charges were detonated, and the shock and acoustic waves were detected with pressure and infrasound sensors stationed at various distances from the source, i.e., from 3 m to 14.5 km. One objective of the experiment was to investigate the evolution of the shock wave produced by the explosion to the acoustic wavefront detected several kilometers from the detonation site. Another objective was to compare the effectiveness of different wind filter strategie
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