Detonation waves are supersonic combustion waves that have a multi-shock front structure followed by a spatially non-uniform reaction zone. During propagation, a de-coupled shock-flame complex is periodically re-initiated into an overdriven detonation following a transient Mach reflection process. Past researchers have identified mechanisms that can increase combustion rates and cause localized hot spot re-ignition behind the Mach shock. But due to the small length scales and stochastic behaviour of detonation waves, the important mechanisms that can lead to re-initiation into a detonation requires further clarification. If a detonation is allowed to diffract behind an obstacle, it can quench to form a de-coupled shock-flame complex and if allowed to form a Mach reflection, re-initiation of a detonation can occur. The use of this approach permits the study of re-initiation mechanisms reproducibly with relatively large length scales. The objective of this study is to experimentally elucidate the key mechanisms that can increase chemical reaction rates and sequentially lead to re-initiation of a de-coupled shock-flame complex into an overdriven detonation wave following a Mach reflection. All experiments were carried out in a thin rectangular channel using a stoichiometric mixture of oxy-methane. Three different types of obstacles were used - a half-cylinder, a roughness plate along with the half-cylinder and a full-cylinder. Schlieren visualization was achieved by using a Z-configuration setup, a high speed camera and a high intensity light source. Results indicate that forward jetting of the slip line behind the Mach stem can potentially increase combustion rates by entraining hot burned gas into unburned gas. Following ignition and jet entrainment, a detonation wave first appears along the Mach stem. The transverse wave can form a detonation wave due to rapid combustion of unburned gas which may be attributed to shock interaction with the unburned gas. Alternatively, the Kelvin-Helmholtz instability can produce vortices along the slipline that may lead to mixing between burned-unburned gases and potentially increase combustion rates near the transverse wave. However, the mechanism(s) that causes the transverse wave to re-initiate into a detonation wave remains to be satisfactorily resolved.

Thesis (Ph. D.)--Ohio State University, 2006. / Title from first page of PDF file. Includes bibliographical references (p. 211-230).

Detonation waves are supersonic combustion waves that have a multi-shock front structure followed by a spatially non-uniform reaction zone. During propagation, a de-coupled shock-flame complex is periodically re-initiated into an overdriven detonation following a transient Mach reflection process. Past researchers have identified mechanisms that can increase combustion rates and cause localized hot spot re-ignition behind the Mach shock. But due to the small length scales and stochastic behaviour of detonation waves, the important mechanisms that can lead to re-initiation into a detonation requires further clarification. If a detonation is allowed to diffract behind an obstacle, it can quench to form a de-coupled shock-flame complex and if allowed to form a Mach reflection, re-initiation of a detonation can occur. The use of this approach permits the study of re-initiation mechanisms reproducibly with relatively large length scales. The objective of this study is to experimentally elucidate the key mechanisms that can increase chemical reaction rates and sequentially lead to re-initiation of a de-coupled shock-flame complex into an overdriven detonation wave following a Mach reflection. All experiments were carried out in a thin rectangular channel using a stoichiometric mixture of oxy-methane. Three different types of obstacles were used - a half-cylinder, a roughness plate along with the half-cylinder and a full-cylinder. Schlieren visualization was achieved by using a Z-configuration setup, a high speed camera and a high intensity light source. Results indicate that forward jetting of the slip line behind the Mach stem can potentially increase combustion rates by entraining hot burned gas into unburned gas. Following ignition and jet entrainment, a detonation wave first appears along the Mach stem. The transverse wave can form a detonation wave due to rapid combustion of unburned gas which may be attributed to shock interaction with the unburned gas. Alternatively, the Kelvin-Helmholtz instability can produce vortices along the slipline that may lead to mixing between burned-unburned gases and potentially increase combustion rates near the transverse wave. However, the mechanism(s) that causes the transverse wave to re-initiate into a detonation wave remains to be satisfactorily resolved.

<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 propellants respectively. Quantification of injector refill times was possible through the use of a high-speed camera recording at a frame rate of 460,000 frames per second. High frequency pressure measurements in both the gaseous and liquid manifolds allow for quantification of the temporal pressure response of the injectors. Variations in simulant mass flow rates, measured through the use of sonic nozzles and cavitating venturis, produce pressure drops up to 262 psi across the injector. Injector refill times are found to be a strong function of the impulse delivered across the injector. Manifold acoustics were found to play a large role in injector response as manifolds that promote manifold over-pressurizations during the injector recovery period recover quicker than designs that limit this response.</p>

Finite amplitude perturbations in compressible media are ubiquitous in scientific and engineering applications such as gas-turbine engines, rocket propulsion systems, combustion instabilities, inhomogeneous solids, and traffic flow prediction models, to name a few. Small amplitude waves in compressible fluids propagate as sound and are very well described by linear theory. On the other hand, the theory of nonlinear acoustics, concerning high-amplitude wave propagation (Mach<2) is relatively underdeveloped. Most of the theoretical development in nonlinear acoustics has focused on wave steepening and has been centered around the Burgers' equation, which can be extended to nonlinear acoustics only for purely one-way traveling waves. In this dissertation, theoretical and computational developments are discussed with the objective of advancing the multi-fidelity modeling of nonlinear acoustics, ranging from quasi one-dimensional high-amplitude waves to combustion-induced detonation waves. <br> <br> We begin with the theoretical study of spectral energy cascade due to the propagation of high amplitude sound in the absence of thermal sources. To this end, a first-principles-based system of governing equations, correct up to second order in perturbation variables is derived. The exact energy corollary of such second-order system of equations is then formulated and used to elucidate the spectral energy dynamics of nonlinear acoustic waves. We then extend this analysis to thermoacoustically unstable waves -- i.e. amplified as a result of thermoacoustic instability. We drive such instability up until the generation of shock waves. We further study the nonlinear wave propagation in geometrically complex case of waves induced by the spark plasma between the electrodes. This case adds the geometrical complexity of a curved, three-dimensional shock, yielding vorticity production due to baroclinic torque. Finally, detonation waves are simulated by using a low-order approach, in a periodic setup subjected to high pressure inlet and exhaust of combustible gaseous mixture. An order adaptive fully compressible and unstructured Navier Stokes solver is currently under development to enable higher fidelity studies of both the spark plasma and detonation wave problem in the future. <br>

This thesis is concerned with experimental and computational studies on pulse detonation engine (PDE) that has been envisioned as a new concept engine. These engines use the high pressure generated by detonation wave for propulsion. The cycle efficiency of PDE is either higher in comparison to conventional jet engines or at least has similar high performance with much greater simplicity in terms of components. The first part of the work consists of an experimental study of the performance of PDE under choked flame and partial fill conditions. Detonations used in classical PDEs create conditions of Mach numbers of 4-6 and choked flames create conditions in which flame achieves Mach numbers near-half of detonation wave. While classical concepts on PDE's utilize deflagration-to-detonation transition and are more intensively studied, the working of PDE under choked regime has received inadequate attention in the literature and much remains to be explored. Most of the earlier studies claim transition to detonation as success in the working of the PDE and non-transition as failure. After exploring both these regimes, the current work brings out that impulse obtained from the wave traveling near the choked flame velocity conditions is comparable to detonation regime. This is consistent with the understanding from the literature that CJ detonation may not be the optimum condition for maximum specific impulse. The present study examines the details of working of PDE close to the choked regime for different experimental conditions, in comparison with other aspects of PDEs. The study also examines transmission of fast flames from small diameter pipe into larger ducts. This approach in the smaller pipe for flame acceleration also leading to decrease in the time and length of transition process. The second part of the study aims at elucidating the features of deflagration-to-detonation transition with direct numerical simulation (DNS) accounting for and the choice of full chemistry and DNS is based on two features: (a) the induction time estimation at the conditions of varying high pressure and temperature behind the shock can only be obtained through the use of full chemistry, and (b) the complex effects of fine scale of turbulence that have sometimes been argued to influence the acceleration phase in the DDT cannot be captured otherwise. Turbulence in the early stages causes flame wrinkling and helps flame acceleration process. The study of flame propagation showed that the wrinkling of flame has major effect on the final transition phase as flame accelerates through the channel. Further, flame becomes corrugated prior to transition. This feature was investigated using non-uniform initial conditions. Under these conditions the pressure waves emanating from corrugated flame interact with the shock moving ahead and transition occurs in between the flame and the forward propagating shock wave. The primary contributions of this thesis are: (a) Elucidating the phenomenology of choked flames, demonstrating that under partial fill conditions, the specific impulse can be superior to detonations and hence, allowing for the possibility of choked flames as a more appropriate choice for propulsive purposes instead of full detonations, (b) The use of smaller tube to enhance the flame acceleration and transition to detonation. The comparison with earlier experiments clearly shows the enhancements achieved using this method, and (c) The importance of the interaction between pressure waves emanating from the flame front with the shock wave which leads to formation of hot spots finally transitioning to detonation wave.

Plusieurs évènements astrophysiques comme les novae, les supernovae de type Ia (SNeIa) et les sursauts X sont le résultat d'une combustion thermonucléaire explosive dans un plasma stellaire. Les supernovae comptent parmi les objets astrophysiques les plus fascinants tant sur le plan théorique que sur celui des observations. Au moment de l'explosion, la luminosité d'une supernova peut égaler celle de l'intégralité des autres étoiles de la galaxie. On admet aujourd’hui que les SNeIa résultent de l'explosion thermonucléaire d'une étoile naine blanche, un objet dense et compact composé de carbone et d'oxygène. Divers chemins évolutifs peuvent conduire à l’explosion de la naine blanche si celle-ci est membre d’un système stellaire binaire. Néanmoins, la nature du système binaire, les mécanismes d'amorçage et de propagation de la combustion thermonucléaire ainsi que le rapport carbone/oxygène au sein de l'étoile compacte ne sont pas encore clairement identifiés à ce jour. En ce qui concerne l’écoulement réactif, on invoque ainsi une détonation (Modèle sub-Chandrasekhar), une déflagration ou la transition d'une déflagration vers une détonation (Modèle Chandrasekhar). La détonation semble donc jouer un rôle prépondérant dans l'explication des SNeIa. <p>Les difficultés de modélisation des détonations proviennent essentiellement (i) de la libération d'énergie en plusieurs étapes, de l’apparition d’échelles de temps et de longueurs caractéristiques très différentes (ii) des inhomogénéités de densité, de température et de composition du milieu dans lequel se propage le front réactif et qui donnent naissance aux structures cellulaires et autres instabilités de propagation du front (extinctions et réamorçages locaux). <p>En plus de celles citées ci-dessus, deux autres difficultés majeures inhérentes à l'étude de ce mode de propagation dans les plasmas stellaires sont rencontrées :la complexité de l’équation d’état astrophysique et la cinétique nucléaire pouvant impliquer plusieurs milliers de nucléides couplés par plusieurs milliers de réactions. Ainsi, les premiers travaux impliquant une combustion thermonucléaire explosive ont été réalisés sur bases d'hypothèses simplificatrices comme l'équilibre nucléaire statistique instantané des produits de réactions ou l'utilisation d'un réseau réduit à une dizaine d'espèces nucléaires. Dans tous ces travaux, la détonation est assimilée à une discontinuité totalement réactive (détonation de Chapman-Jouguet ou CJ). La résolution de l'onde de détonation nécessite l'étude détaillée du processus nucléaire se déroulant dans la zone de réaction. Malheureusement, les supports de calculs actuels ne permettent pas encore ce type de simulations pour les détonations astrophysiques. Le modèle ZND qui constitue une description unidimensionnelle stationnaire de l’écoulement (plan ou courbé) constitue une excellente approximation de la réalité. <p>Notre travail réexamine les résultats des calculs des structures des ondes de détonations stellaires dans les conditions de température, de densité et de composition envisagées dans les travaux de ce type (détonation CJ et ZND) réalisés jusqu’à présent mais avec une équation d’état appropriée aux plasmas stellaires et une cinétique nucléaire nettement plus riche ;le plus grand réseau jamais utilisé pour ce genre d’études (333 noyaux couplés par 3262 réactions), prenant en compte les données les plus récentes de la physique nucléaire (vitesses de réaction et fonctions de partition)./Several astrophysics events like novae, supernovae and X burts, result from an explosive thermonuclear burning in stellar plasma. Type Ia Supernovae (SNeIa) count amoung the most fascinating stellar objects, they can be more brighter than an entire galaxy. Astrophysic works show that SNeIa may result from a thermonuclear explosion of a compact and dense star called carbon-oxygen white dwarf. The ignition stage and the propagation mode of the thermonuclear combustion wave are not identified yet. The Deflagration-to-Detonation Transition process (or "delayed detonation") sims to give the best overall agrements with the observations :detonations can play appart in SNeIa events. <p><p>Simulating thermonuclear detonations count same difficults. The most important are the burning length scales that spent over more than ten oders of magnitud, the nuclear kinetics that involve thousands of nuclids linked by thousands of nuclear reactions and the stellar plasma equation of state (EOS). Hydrodynamical simulations of detonation use very simplified ingedients like reduced reactions network and asymptotic EOS of completely electron degenerate stellar plasma.<p><p>Our work is the modelling of these detonations using more representative EOS of the stallar plasma that includs ions, electrons, radiation and electron-pistron pairs. We also use a more <p>detailed kinetic network, comprising 331 nuclids linked by 3262 capture and photodisintegration reactions, than those usualy employed.<p> <p> / Doctorat en Sciences / info:eu-repo/semantics/nonPublished