Thermodynamics of a Rotating Detonation Engine PDF Download
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Author: Craig A. Nordeen
Publisher:
ISBN:
Category :
Languages : en
Pages : 201
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Author: Craig A. Nordeen
Publisher:
ISBN:
Category :
Languages : en
Pages : 201
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Book Description
Author: Jiun-Ming Li
Publisher: Springer
ISBN: 3319689061
Category : Technology & Engineering
Languages : en
Pages : 246
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Book Description
This book focuses on the latest developments in detonation engines for aerospace propulsion, with a focus on the rotating detonation engine (RDE). State-of-the-art research contributions are collected from international leading researchers devoted to the pursuit of controllable detonations for practical detonation propulsion. A system-level design of novel detonation engines, performance analysis, and advanced experimental and numerical methods are covered. In addition, the world’s first successful sled demonstration of a rocket rotating detonation engine system and innovations in the development of a kilohertz pulse detonation engine (PDE) system are reported. Readers will obtain, in a straightforward manner, an understanding of the RDE & PDE design, operation and testing approaches, and further specific integration schemes for diverse applications such as rockets for space propulsion and turbojet/ramjet engines for air-breathing propulsion. Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines provides, with its comprehensive coverage from fundamental detonation science to practical research engineering techniques, a wealth of information for scientists in the field of combustion and propulsion. The volume can also serve as a reference text for faculty and graduate students and interested in shock waves, combustion and propulsion.
Author: J. A. C. Kentfield
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Robert Francis Burke
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Conventional engines are limited by the efficiency of their combustion mode. Compared to present constant pressure deflagration-based engines, detonation-based systems can realize a higher thermodynamic cycle efficiency, making them an attractive candidate for next generation propulsion systems that will take humanity to hypersonic speeds and even to Mars. For all its performance gains, detonation engines are still far off from implementation. One system, the rotating detonation engine (RDE) is promising as a detonation-based engine concept for its stability, simplicity, and versatility. For these reasons, RDEs have been the subject of studies internationally in efforts to understand their operation and integration into conventional technology. RDEs are on the cusp of field use, considered at technology readiness level 5 with prototype demonstrations occurring today; however, there are still significant barriers holding back this technology from widespread adoption. The work of this dissertation confronts each of these barriers with experimental methods. Using multiple different RDE test facilities, investigations into injection, fueling, exhaust, detonability, and integration were conducted, targeting research gaps in each barrier. As a result, many novel advancements have been made from these studies such as the first demonstration of hydrogen and oxygen rotating detonations, the detonability of sustainable solid particle fuels, and the effect of fuel stratification on rotating detonation propagation. Altogether, the work presented depicts the RDE from a complete perspective by advancing current RDE research through multiple channels with the intention of advancing the technology readiness level of RDEs.
Author: John H. S. Lee
Publisher: Cambridge University Press
ISBN: 9780521897235
Category : Technology & Engineering
Languages : en
Pages : 400
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Book Description
This book introduces the detonation phenomenon in explosives. It is ideal for engineers and graduate students with a background in thermodynamics and fluid mechanics. The material is mostly qualitative, aiming to illustrate the physical aspects of the phenomenon. Classical idealized theories of detonation waves are presented first. These permit detonation speed, gas properties ahead and behind the detonation wave, and the distribution of fluid properties within the detonation wave itself to be determined. Subsequent chapters describe in detail the real unstable structure of a detonation wave. One-, two-, and three-dimensional computer simulations are presented along with experimental results using various experimental techniques. The important effects of confinement and boundary conditions and their influence on the propagation of a detonation are also discussed. The final chapters cover the various ways detonation waves can be formed and provide a review of the outstanding problems and future directions in detonation research.
Author: Andrew Ryan Mizener
Publisher:
ISBN:
Category : Acoustic phenomena in nature
Languages : en
Pages : 226
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Book Description
The rotating detonation engine (RDE) is a promising propulsion concept that has the potential to offer increased thermodynamic performance in a compact package with no moving parts. A series of analytical and experimental investigations was carried out on RDEs with the joint goal of investigating swirl, torque, and a range of other design parameters of interest. The model and experimental facility were then applied to related problems with the goal of advancing the understanding of RDE applications. A flexible, low-order, semi-empirical model for a rotating detonation engine was presented. The model was formulated to be able to run broad parametric analyses more efficiently than numerical modeling. The presence of swirl at the exit plane of RDEs is still debated, so the model was formulated to leave open this possibility. Parametric analysis was conducted to determine the effect of a range of engine design parameters on performance. Exit swirl and torque were shown to be small but not uniquely zero. The model was combined with a waverider forebody model. Together, these were used to conduct parametric analysis of the sensitivity of integrated performance to freestream, waverider forebody, and RDE design parameters. Practical limitations on the Mach number of detonation engines operating in supersonic flows were presented and discussed. Peak performance was seen at the point of maximum forebody pressure recovery. Thrust and torque were shown to be sensitive to body shape and freestream parameters, while specific impulse and thrust-specific fuel consumption were not. The design of a rotating detonation engine and experimental test facility were presented and discussed. The facility was designed and instrumented to allow the measurement of resultant torque on the engine as well as take thrust and pressure readings. A series of tests was conducted using the engine, with no steadily-propagating detonation waves detected. Pressure, torque, thrust, and frequency data were presented and discussed. A high-speed camera was used to visualize the exhaust plume and the flame structure inside the annulus, which similarly failed to detect a detonation wave. The camera was then used to conduct high-speed visualizations of the ignition process inside the engine for both spark plug and predetonator igniters. Both methods showed the creation of two counter-rotating detonation waves which intersected and canceled each other out on the far side of the annulus. Pressure waves were observed to continue to rotate for several periods before dying out. The qualitative observations from the visualizations were supported by the pressure data. Detailed visualizations were performed to quantitatively investigate the propagation of the initial combustion front around the annulus for varying degrees of injector swirl. Predetonator ignition was observed to directly initiate a detonation, whereas deflagration-to-detonation transition was observed for spark plug ignition. Injector swirl promoted transition in combustion waves propagating into the swirl and depressed it in waves propagating with the swirl. Overdriven detonations were observed for both ignition methods. A discussion of the possible causes for the failure to sustain a detonation wave was presented and discussed.
Author: Henry Clyde Foust III
Publisher: Springer Nature
ISBN: 3030873870
Category : Science
Languages : en
Pages : 408
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Book Description
This textbook provides students studying thermodynamics for the first time with an accessible and readable primer on the subject. The book is written in three parts: Part I covers the fundamentals of thermodynamics, Part II is on gas dynamics, and Part III focuses on combustion. Chapters are written clearly and concisely and include examples and problems to support the concepts outlined in the text. The book begins with a discussion of the fundamentals of thermodynamics and includes a thorough analysis of engineering devices. The book moves on to address applications in gas dynamics and combustion to include advanced topics such as two-phase critical flow and blast theory. Written for use in Introduction to Thermodynamics, Advanced Thermodynamics, and Introduction to Combustion courses, this book uniquely covers thermodynamics, gas dynamics, and combustion in a clear and concise manner, showing the integral connections at an advanced undergraduate or graduate student level.
Author: James Koch
Publisher:
ISBN:
Category : Detonation waves
Languages : en
Pages : 147
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Book Description
The Rotating Detonation Engine (RDE) is a novel rocket combustor configuration that features a periodic, high aspect ratio (length of flowpath versus transverse thickness) combustion chamber designed to promote tangential high-frequency combustion instabilities typical of conventional rockets. Most RDEs are comprised of concentric cylinders whereby the annular gap between the cylinders constitutes the flow domain. The annular gap acts as geometric confinement suitable for robustly promoting the self-steepening of pressure and density gradients caused by combustion. The RDE's steady operation is the saturation of this highly nonlinear self-steepening process: a number of circumferentially traveling detonation waves. The benefits of the RDE include a larger stable operating envelope and potentially higher thermodynamic cycle efficiency over conventional rockets. However, the collective behavior of the detonation waves present in the RDE combustion chamber, while readily observable, is not well understood nor sufficiently characterized, especially with respect to engineering metrics such as thrust or engine stability. This dissertation is a comprehensive experimental, theoretical, and numerical study that aims to link observed the gasdynamic engine behavior to the nonlinear dynamics of the detonation waves. The experimental test campaign features engines of two sizes: a 154-mm flowpath outer diameter (OD) engine and a 76mm OD engine. A sweep of boundary conditions (inlet and outlet pressures) was conducted using the 154-mm RDE at reduced mass flux conditions to establish the engine0́9s gasdynamic operating regimes, namely the attainment of a thermal choke at the exit of the annular duct. Similarly, using the 76-mm RDE at elevated mass flux conditions, the engine0́9s response to the attainment of an axial thermal choke is investigated with respect to changes in total injection area. From both sets of testing, found is that the choked annular duct acts as a boundary condition that fixes the upstream pressure required to steadily deliver a given mass flow rate of propellant of a specified chemical energy potential. By recording the space-time history of the detonation waves with a high speed camera, a diverse set of behavior was recorded and collected during the experimental test campaign. Such behavior includes wave nucleation, destruction, mode-locking of multiple waves, persistent wave modulation, and pulsating plane waves. By drawing upon the well-established fields of nonlinear waves and detonation analog modeling, a Rotating Detonation Engine analog system is proposed. This model system is an adaptation of the Majda detonation analog to a periodic domain with imposed dissipation and propellant regeneration. The dissipative process is constrained to enforce the same global behavior seen in experiments, namely the self-similar pressure operating profiles attained with a thermal choke point at the exit of the engine. Within the reduced-scope of co-rotating detonation waves, the RDE analog system is found to qualitatively reproduce all transients and modes of operation seen in experiments. The propagating waves are classified as autosolitons, or localized structures with offsetting dominant balance physics. Within this context, the dominant balance physics are identified and found to be strongly influenced by input-output energy dynamics and act across several orders of spatial and temporal scales. In this manner, the global multi-scale balance physics give rise to the traveling detonation waves and their associated dynamics - not exclusively the frontal dynamics prescribed by classical detonation theory. Furthermore, the underlying fundamental Hopf bifurcation to time-periodic modulation of the collection of waves is confirmed to exist in the RDE analog. Comparisons between computed Hopf orbits of the model and experimentally-extracted kinematic traces are made showing good qualitative agreement.
Author: Pinku Debnath
Publisher:
ISBN:
Category : Electronic books
Languages : en
Pages : 0
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Book Description
Pulse detonation engines (PDEs) are most exciting for future propulsion generation. Detonation combustion in pulse detonation combustor is an energetic combustion process which is differs from other combustion process. The detonation wave propagation in detonation tube is a pulse setting combustion phenomena. Detonation combustion process is thousands times faster than deflagration combustion process. PDE utilizes several pulse of detonation wave to produce propulsive force. The potential applications of PDEs are drastically reduces the cost of orbit transfer vehicle system and flying mode applications. Of course it can be used as ground level applications also. Draw back are DDT in shortest possible time in the combustor. In this regards, worldwide researchers are focusing on scientific and technical issues related to improvement of PDC. The present chapter deals with review study on detonation combustion process, historical overview on chemical kinetics, calorimetric and entropy transport, energy and exergy analysis and factor effecting on deflagration to detonation transition with recommendable future research.
Author: Zonglin Jiang
Publisher: Springer Nature
ISBN: 9811970025
Category : Science
Languages : en
Pages : 281
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Book Description
This book highlights the theories and research progress in gaseous detonation research, and proposes a universal framework theory that overcomes the current research limitations. Gaseous detonation is an extremely fast type of combustion that propagates at supersonic speed in premixed combustible gas. Being self-sustaining and self-organizing with the unique nature of pressure gaining, gaseous detonation and its gas dynamics has been an interdisciplinary frontier for decades. The research of detonation enjoyed its early success from the development of the CJ theory and ZND modeling, but phenomenon is far from being understood quantitatively, and the development of theories to predict the three-dimensional cellular structure remains a formidable task, being essentially a problem in high-speed compressible reacting flow. This theory proposed by the authors’ research group breaks down the limitation of the one-dimensional steady flow hypothesis of the early theories, successfully correlating the propagation and initiation processes of gaseous detonation, and realizing the unified expression of the three-dimensional structure of cell detonation. The book and the proposed open framework is of high value for researchers in conventional applications such as coal mine explosions and chemical plant accidents, and state-of-the-art research fields such as supernova explosion, new aerospace propulsion engines, and detonation-driven hypersonic testing facilities. It is also a driving force for future research of detonation.
