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Thematische Bibliographien / Rotating Detonations / Dissertationen

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Dissertationen zum Thema „Rotating Detonations“

Autor: Grafiati

Veröffentlicht am 4. Juni 2021

Zuletzt aktualisiert am 6. Februar 2022

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1

Geller, Alexander C. "Thermal Imaging of RDCs and the Characterization of an Operating Map for a Novel RDC Geometry." University of Cincinnati / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin161368598622062.

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2

Anand, Vijay G. "Rotating Detonation Combustor Mechanics." University of Cincinnati / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1530798871271548.

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3

Lim, Wei Han Eugene. "Gasdynamic inlet isolation in rotating detonation engine." Thesis, Monterey, California. Naval Postgraduate School, 2010. http://hdl.handle.net/10945/5068.

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Includes supplementary material<br>Approved for public release; distribution is unlimited<br>The Rotating Detonation Engine (RDE) concept represents the next-generation of detonation-based engines as it provides higher performance and near constant thrust with a simpler overall design. Since RDE systems are in the early stage of development, the physics of engine design is yet to be fully understood and developed. A critical concern of these systems is the practical isolation of the reactant injection manifold and supply system from the combustor pressure oscillations. For this study, the

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4

St, George Andrew. "Development and Testing of Pulsed and Rotating Detonation Combustors." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1458893231.

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5

Driscoll, Robert B. "Investigation of Sustained Detonation Devices: the Pulse Detonation Engine-Crossover System and the Rotating Detonation Engine System." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1459155478.

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6

Jodele, Justas B. "Impacts of Geometrical Variations on Rotating Detonation Combustors and Pulsejets." University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1560866939025106.

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7

Raj, Piyush. "Influence of Fuel Inhomogeneity and Stratification Length Scales on Detonation Wave Propagation in a Rotating Detonation Combustor (RDC)." Thesis, Virginia Tech, 2021. http://hdl.handle.net/10919/103185.

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The detonation-based engine has the key advantage of increased thermodynamic efficiency over the traditional constant pressure combustor. These detonation-based engines are also known as Pressure Gain Combustion systems (PGC) and Rotating Detonation Combustor (RDC) is a form of PGC, in which the detonation wave propagates azimuthally around an annular combustor. Prior researchers have performed a high fidelity 3-D numerical simulation of a rotating detonation combustor (RDC) to understand the flow physics such as detonation wave velocity, pressure profile, wave structure; however, performing t

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8

Knight, Ethan. "Effect of Corrugated Outer Wall On Operating Regimes of Rotating Detonation Combustors." University of Cincinnati / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1523631068586522.

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9

North, Gary S. "Metal Coupon Testing in an Axial Rotating Detonation Engine for Wear Characterization." Wright State University / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=wright1588770787704665.

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10

Subramanian, Sathyanarayanan. "Novel Approach for Computational Modeling of a Non-Premixed Rotating Detonation Engine." Thesis, Virginia Tech, 2019. http://hdl.handle.net/10919/101777.

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Detonation cycles are identified as an efficient alternative to the Brayton cycles used in power and propulsion applications. Rotating Detonation Engine (RDE) operating on a detonation cycle works by compressing the working fluid across a detonation wave, thereby reducing the number of compressor stages required in the thermodynamic cycle. Numerical analyses of RDEs are flexible in understanding the flow field within the RDE, however, three-dimensional analyses are expensive due to the differences in time-scale required to resolve the combustion process and flow-field. The alternate two-dimens

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11

Suchocki, James Alexander. "Operational Space and Characterization of a Rotating Detonation Engine Using Hydrogen and Air." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1330266587.

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12

Wilhite, Jarred M. "Investigation of Various Novel Air-Breathing Propulsion Systems." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin147981623341895.

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13

Zhu, Yonry R. "Applications and Modeling of Non-Thermal Plasmas." Ohio University Honors Tutorial College / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ouhonors1492777535797122.

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14

Gaillard, Thomas. "Étude numérique du fonctionnement d’un moteur à détonation rotative." Thesis, Université Paris-Saclay (ComUE), 2017. http://www.theses.fr/2017SACLC011/document.

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Cette thèse s’inscrit dans le domaine de la simulation numérique appliquée à la propulsion. Le moteur à détonation rotative (RDE) fait partie des candidats susceptibles de remplacer nos actuels moyens de propulsion grâce à l’augmentation du rendement thermodynamique du moteur. Pour conserver l’avantage de la détonation, l’injecteur doit fournir un mélange dont la qualité doit être la meilleure possible tout en limitant les pertes de pression totale. La présente étude porte sur le développement et l’optimisation numérique d’un injecteur adapté au fonctionnement d’un RDE. L’injection d’hydrogène

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15

Blümner, Richard [Verfasser], Christian Oliver [Akademischer Betreuer] Paschereit, Myles D. [Akademischer Betreuer] Bohon, et al. "Operating mode dynamics in rotating detonation combustors / Richard Blümner ; Gutachter: Christian Oliver Paschereit, Myles D. Bohon, Antonio Andreini, Marc Bellenoue ; Christian Oliver Paschereit, Myles D. Bohon, Ephraim J. Gutmark." Berlin : Technische Universität Berlin, 2020. http://d-nb.info/1214708919/34.

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16

Hansmetzger, Sylvain. "Etude des modes de rotation continue d'une détonation dans une chambre annulaire de section constante ou croissante." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2018. http://www.theses.fr/2018ESMA0002/document.

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Notre étude vise à améliorer la compréhension des modes de rotation continue d’une détonation. Elle porte sur leur caractérisation dans une chambre annulaire de section,normale à son axe de révolution, constante ou linéairement croissante. Le principe de fonctionnement repose sur l’injection continue de gaz frais devant le front de détonation pour renouveler la couche réactive et entretenir sa propagation. Ce travail trouve son application dans le développement de systèmes propulsifs utilisant la détonation rotative comme mode de combustion (Rotating Detonation Engine, RDE). Nous avons conçu e

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17

(11014821), Ian V. Walters. "Operability and Performance of Rotating Detonation Engines." Thesis, 2021.

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<div>Rotating Detonation Engines (RDEs) provide a promising avenue for reducing greenhouse gas emissions from combustion-based propulsion and power systems by improving their thermodynamic efficiency through the application of pressure-gain combustion. However, the thermodynamic and systems-level advantages remain unrealized due to the challenge of harnessing the tightly coupled physics and nonlinear detonation dynamics inherent to RDEs, particularly for the less-detonable reactants characteristic of applications. Therefore, a RDE was developed to operate with natural gas and air as the primar

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18

(6927776), Alexis Joy Harroun. "Investigation of Nozzle Performance for Rotating Detonation Rocket Engines." Thesis, 2019.

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Progress in conventional rocket engine technologies, based on constant pressure combustion, has plateaued in the past few decades. Rotating detonation engines (RDEs) are of particular interest to the rocket propulsion community as pressure gain combustion may provide improvements to specific impulse relevant to booster applications. Despite recent significant investment in RDE technologies, little research has been conducted to date into the effect of nozzle design on rocket application RDEs. Proper nozzle design is critical to capturing the thrust potential of the transient pressure ratios pr

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19

(6634439), Christopher Lee Journell. "High-Speed Diagnostics in a Natural Gas-Air Rotating Detonation Engine at Elevated Pressure." Thesis, 2019.

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<div>Gas turbine engines have operated on the Brayton cycle for decades, each decade only gaining approximately one to two percent in thermal efficiency as a result of efforts</div><div>to improve engine performance. Pressure-gain combustion in place of constant-pressure combustion in a Brayton cycle could provide a drastic step-change in the thermal efficiency of these devices, leading to reductions in fuel consumption and emissions production. Rotating Detonation Engines (RDEs) have been widely researched as a viable option for pressure-gain combustion. Due to the extremely high frequencies

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20

(6866786), Timothy P. Gurshin. "Heating and Regenerative Cooling Model for a Rotating Detonation Engine Designed for Upper Stage Performance." Thesis, 2019.

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<div>Rotating detonation engines (RDE) have the potential to significantly advance the efficiency of chemical propulsion. They are approximately one order of magnitude shorter than constant pressure engines, a savings benefit that is especially important for upper stage engines. There are many challenges to advancing their technological readiness level, but one area this thesis attempts to help mitigate is the understanding of heat loads and the viability of regenerative jacket cooling.<br></div><div> A one-dimensional, steady-state heat transfer and regenerative cooling model for the upper

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21

(9505169), Kevin James Dille. "Transient Response of Gas-Liquid Injectors Subjected to Transverse Detonation Waves." Thesis, 2020.

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<p>A series of experimental tests were performed to study the transient response of gas/liquid injectors exposed to transverse detonation waves. A total of four acrylic injectors were tested to compare the response between gas/liquid and liquid only injectors, as well as compare the role of various geometric features of the notional injector design. Detonation waves are produced through the combustion of ethylene and oxygen, at conditions to produce average wave pressures between 128 and 199 psi. The injectors utilize water and nitrogen to simulate the injection of liquid and gaseous propellan

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22

(8037983), Dasheng Lim. "Experimental Studies of Liquid Injector Response and Wall Heat Flux in a Rotating Detonation Rocket Engine." Thesis, 2019.

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<div>The results of two experimental studies are presented in this document. The first is an investigation on the transient response of plain orifice liquid injectors to transverse detonation waves at elevated pressures of 414, 690, and 1,030 kPa (60, 100, and 150 psia). Detonations were produced using a predetonator which utilized hydrogen and</div><div>oxygen or ethylene and oxygen as reactants. For injectors of identical diameter, an increase in length correlated with a decrease in the maximum back-flow distance. A preliminary study using an injector of larger diameter suggested that for in

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23

(11199204), Kyle S. Schwinn. "Characteristics of Periodic Self-sustained Detonation Generation in an RDE Analogue." Thesis, 2021.

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<div>Rotating detonation engines (RDEs) are one of the most promising options for improving combustor efficiency through a constant-volume combustion process. RDEs are characterized by continuous detonation propagation in an annular combustion chamber with an implicitly dynamic injection response. An additional benefit is the similarity of these devices to existing engine architectures. However, RDEs have yet to realize their thermodynamic and systemic advantages due the non-ideal physics of detonation in practical devices and the complex interactions between the detonations and the hydrodynam

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24

(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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