[EN] Since the last two decades of the XX century and still nowadays the automotive industry has resorted to the very understanding of the combustion process. Regarding the Diesel engine many contributions has been built from the machine itself or test rigs that simulate real operating conditions. Based on that, the use of non-intrusive optical techniques has propelled the understanding of Diesel combustion phenomena, and extended conceptual models as Dec stablishes the Diesel flame morphology from the visualization of the injection/combustion process. From such combustion process picture, a review of the current state of the art has been done in order to assess on the still remain questions of the injection/combustion areas open to knowledge contribution. In that sense, it has been identified that Diesel flame transient evolution turns contradictory either on the final penetration result or the difficulties involved with reacting spray studies. While the quantification of the soot and its temperature in diffusive conditions might be related with high uncertainties of the experimental set-up, i.e. with the final result. The approach of this thesis is experimental; therefore, it considers the experimental conditions to ideally address the investigation with two main optical techniques, schlieren visualization and the two color method. Regarding the first one, the solution to saturation of the camera sensor enabled a reliable penetration on the reacting spray penetration. This technique added value has helped to evaluate two different test rigs in order to define the ideal environment (optical technique + test rig) to better describe the reacting spray. Regarding two color thermometry, experimental calibration has helped to define the basis to obtain a spatial relationship of images with different spectral information and to significantly improve the technic results. As a result, using standard techniques to investigate lift-off length of diffusion flames has helped to establish that the schlieren image with temporal resolution is feasible from the radial expansion in the auto-ignition area. Schlieren results: penetration, inert and reactive spray angle and lift-off have supported the description of the evolution of penetration flame phases, which compared with an inert jet have been modified by the establishment of the combustion. Depending on the radial and axial flame expansion the process description can be modified according to the variation of combustion conditions. Although, in the overall description framework the 5 stages of penetration: inert, self-ignition and expansion, stabilization, acceleration and quasi stationarity are kept. On the other hand, research on competing fuels in the formation of soot as n-heptane and Diesel, has helped to establish the sensitivity of soot indicators under different operating conditions evaluated in an optical engine. As an overall, understanding the evolution of the flame front penetration and soot formation in diffusive flames provides an extensive data with which it is possible to feed complex calculation models as the CFD and thus, provide additional elements for comprehending the radial and axial flame expansion processes; something that in the present work has been analyzed only from the macroscopic point of view document. / [ES] A lo largo de las dos últimas décadas del final del siglo XX y aún hasta la actualidad la industria de automoción ha recurrido al entendimiento de los procesos que gobiernan el proceso de combustión. En el caso del motor Diesel, muchos son los aportes que se han construido en tal sentido a partir de estudios sobre el motor propiamente dicho o a través de herramientas que simulan las condiciones de operación de este. Con ello, la introducción de medidas no intrusivas de carácter óptico ha impulsado el entendimiento del fenómeno de combustión Diesel. Conceptos tan amplios como el Dec establecen la morfología de la llama Diesel generados a partir de la visualización del proceso de inyección/combustión. A partir de esta fotografía del proceso de combustión, se ha hecho un revisión de cuál es el estado del arte actual con la finalidad de identificar los aspectos de inyección y combustión que en la literatura permanecen aún abiertos al aporte de conocimiento. En ese sentido, se ha identificado que el conocimiento de la evolución transitoria de llamas Diesel resulta contradictoria, bien por el resultado final de penetración o por la dificultad planteada al estudiar chorros reactivos. Mientras que en condiciones de combustión por difusión, la cuantificación del hollín y su temperatura parece estar relacionada con un alta incertidumbre asociada al desarrollo experimental, en sí, con el resultado final. El enfoque de esta tesis es experimental, y por tanto se plantean las condiciones experimentales para afrontar de manera idónea la investigación con dos técnicas ópticas principales, la visualización schlieren y la termometría de dos colores. Respecto a la primera, la solución al fenómeno de saturación de sensores de cámara de visualización ha permitido establecer una medida fiable de la penetración del chorro reactivo. Este valor agregado a la técnica, ha permitido evaluar dos instalaciones disponibles en el grupo de investigación donde se ha desarrollado la investigado y definir el entorno experimental técnica + instalación ideal para la descripción de evolución transitoria de la llama. Respecto a la termometría de dos colores, la puesta a punto experimental ha permitido establecer las bases para establecer una relación espacial de imágenes con información espectral diferente y mejorar sensiblemente el resultado de la técnica. Como resultados, el apoyo en técnicas estándar para la investigación de la longitud de lift-off de llamas de difusión, ha permito establecer comparativamente que la medida a partir de la imagen de schlieren con resolución temporal es factible a partir de la expansión radial en la zona de autoencendido. Los resultados de schlieren: penetración, ángulo de chorro inerte/reactivo y el lift-off han apoyado la descripción de las fases de la evolución de le penetración de llama, que en comparación con un chorro-inerte se ha visto modificada por el establecimiento de la combustión. Dependiendo de la expansión radial y axial de la llama la descripción del proceso puede modificarse según varían las condiciones de combustión, aunque el marco global de la descripción se mantienen las 5 fases de penetración: Inerte, autoencendido y expansión, estabilización, aceleración y cuasi estacionalidad. Por otra parte, la investigación sobre combustibles contrapuestos en la formación de hollín como el n-Heptano y Diesel, han permitido establecer la sensibilidad de indicadores de la cantidad de hollín y su en diferentes condiciones de operación evaluadas en un motor óptico. En conjunto, el entendimiento de la evolución del penetración del frente y de llama y la formación de hollín en llamas difusivas provee de una matriz de ensayos extensa con la cual es posible alimentar modelos de cálculos complejos como el CFD y así, proporcionar elementos adicionales para el entendimiento de los procesos de expansión radial y axial de la llama. Algo que en e / [CA] Al llarg de les dues últimes dècades del final del segle XX i encara fins a l'actualitat la indústria d'automoció ha recorregut a l'enteniment dels processos que governen el procés de combustió. En el cas del motor Diesel, molts són les aportacions que s'han construït en aquest sentit a partir d'estudis sobre el motor pròpiament dit o a través d'eines que simulen les condicions d'operació d'aquest. Amb això, la introducció de mesures no intrusives de caràcter òptic ha impulsat l'enteniment del fenomen de combustió dièsel. Models conceptuals tan amplis com el de Dec estableixen la morfologia de la flama Diesel generats a partir de la visualització del procés d'injecció / combustió. A partir d'aquesta fotografia del procés de combustió, s'ha fet un revisió de quin és l'estat de l'art actual amb la finalitat d'identificar els aspectes d'injecció i combustió que en la literatura romanen encara oberts a l'aportació de coneixement. En aquest sentit, s'ha identificat que el coneixement de l'evolució transitòria de flames Diesel resulta contradictòria, bé pel resultat final de penetració o per la dificultat plantejada en estudiar dolls reactius. Mentre que en condicions de combustió per difusió, la quantificació del sutge i la seva temperatura sembla estar relacionada amb una alta incertesa associada al desenvolupament experimental, en si, amb el resultat final. L'enfocament d'aquesta tesi és experimental, i per tant es plantegen les condicions experimentals per afrontar de manera idònia la investigació amb dues tècniques òptiques principals, la visualització schlieren i la termometria de dos colors. Respecte a la primera, la solució al fenomen de saturació de sensors de cambra de visualització ha permès establir una mesura fiable de la penetració del doll reactiu. Aquest valor afegit a la tècnica, ha permès avaluar dues instal·lacions disponibles en el grup de recerca on s'ha desenvolupat el treball i definir l'entorn experimental tècnica + instal·lació ideal per a la descripció d'evolució transitòria de la flama. Respecte a la termometria de dos colors, la posada a punt experimental ha permès establir les bases per establir una relació espacial d'imatges amb informació espectral diferent i millorar sensiblement el resultat de la tècnica. Com a resultats, el suport en tècniques estàndard per a la recerca de la longitud de lift-off de flames de difusió, ha permès establir comparativament que la mesura a partir de la imatge de schlieren amb resolució temporal és factible a partir de l'expansió radial en la zona d'autoencesa. Els resultats de schlieren: penetració, angle de doll inert / reactiu i lift-off han donat suport a la descripció de les fases de l'evolució de la penetració de flama, que en comparació amb un doll inert s'ha vist modificada per l'establiment de la combustió. Depenent de l'expansió radial i axial de la flama la descripció del procés pot modificar-se segons varien les condicions de combustió, tot i que en el marc global de la descripció es mantenen les 5 fases de penetració: Inert, autoencesa i expansió, estabilització, acceleració i quasi estacionalitat . D'altra banda, la investigació sobre combustibles contraposats en la formació de sutge com el n-heptà i Diesel, han permès establir la sensibilitat d'indicadors de la quantitat de sutge i la seva en diferents condicions d'operació avaluades en un motor òptic. En conjunt, l'enteniment de l'evolució del penetració del front de flama i la formació de sutge en flames difusives proveeix d'una matriu d'assajos extensa amb la qual és possible alimentar models de càlculs complexos com el CFD i així, proporcionar elements addicionals per l'enteniment dels processos d'expansió radial i axial de la flama. Una cosa que en aquest document s'ha analitzat només des del punt de vista macroscòpic. / Briceño Sánchez, FJ. (2016). APORTACIONES AL ESTUDIO DE LA EVOLUCIÓN TRANSITORIA DE LLAMAS DE DIFUSIÓN DIESEL [Tesis doctoral]. Universitat Politècnica de València. https://doi.org/10.4995/Thesis/10251/61485

<p dir="ltr">The dynamics and characteristics of a high-speed compressible turbulent boundary layer or shear layer have significant effects on separation, heating, shockwave boundary layer interactions, effectiveness of control surfaces, and ultimately the performance of supersonic / hypersonic vehicles. Experimental data with high spatiotemporal resolution and low uncertainty is necessary for understanding complex flow physics and validating computational models. </p><p dir="ltr">Background oriented schlieren (BOS) is a technique derived from traditional schlieren imaging to provide whole-field, quantitative density gradient measurements with a simplistic setup at the expense of reduced spatial resolution and increased uncertainty. The majority of BOS applications focus on low-speed flows with an entocentric optical setup which causes low depth-of-field, wall-blurring, and perspective error issues, making conventional BOS not suitable for high-speed compressible turbulent flow settings. Additionally, despite the widespread adoption of BOS, it has primarily been used as an alternative visualization technique to traditional schlieren imaging and thus the quantitative capabilities of BOS are left under-exploited.</p><p dir="ltr">The workflow of BOS consists of image acquisition, displacement estimation, and integration of the density gradient field. The work presented in this thesis improves the image acquisition and displacement estimation of the BOS workflow by implementing a telecentric optical system and conducting a comprehensive comparison and optimization of several state-of-the-art displacement estimation techniques. Experimental results for a Mach 2 turbulent boundary layer exhibit high spatiotemporal resolution and low uncertainties and are compared against high-fidelity computational results for validation. This work also focuses on the development of BOS velocimetry capabilities, by leveraging ray tracing simulations of an LES turbulent shear layer. Overall this dissertation advances the accuracy, precision, spatial resolution, and capabilities of BOS for fluid dynamic applications relevant to defense and propulsion.</p>

<p>The first force and moment measurements were conducted in the BAM6QT. Three 7-degree half-angle sharp cones were tested, one with base radius of 4.5 in. and two with base radius of 3.5 in. made out of different materials. Models were tested at 0 and 2 degrees angle of attack. Models were tested over a range of burst pressures and Reynolds numbers. Models were fitted onto a strain gauge, 6 component, internal, moment balance. Multiple assemblies were tested that mounted the balance in the BAM6QT. High-speed schlieren video was used to monitor flow conditions and track the movement of the tunnel and model. Three entries were performed in the BAM6QT. The improvement in data quality with each new entry is shown and the startup and running loads from entry 3 are analyzed.</p> <p>Startup loads were measured and are of importance in determining the load range needed to operate in the BAM6QT. Large startup loads up to 40X the running load were identified. Tunnel movement was measured and was used to approximate the inertial loading during startup and the run. The inertial loading was not found to be the cause of the large startup loads. Schlieren video was used to qualitatively review the startup flow. It was found the large startup loads in axial force were plausibly from the high-pressure subsonic flow evacuating the nozzle. For normal force and pitching moment, the startup loads peak at a different time than axial force and appear to be from a shock-shock interaction nearby the model. Trends in startup load with changing model geometry, AoA, and burst pressure were put together to form an empirical estimation for startup loads sharp cones. </p> <p>Running loads were profiled and found to be trending with burst pressure and model geometry similarly to Newtonian flow theory predictions. However, due to the lack of a base pressure measurement, the results are uncorrected for sting effects and differ from Newtonian flow theory by a scalar. A 5.3 Hz oscillation in axial force was identified. The frequency of the oscillation is the same as the frequency of the quasi-steady flow periods caused by the reflection of the expansion fan in the driver tube. Normal force during the running load was found to be measuring positive loads when at 0 degrees angle of attack. Both the axial and normal force phenomena were unexpected and were investigated but both require further research. </p> <p><br></p> <p><br></p> <p><br></p> <p><br></p>

<p>There is growing interest in the use of nanosecond surface dielectric barrier discharge (ns-SDBD) actuators for high-speed (supersonic/hypersonic) flow control. A plasma discharge is created using a nanosecond-duration pulse of several kilovolts, and leads to a rapid heat release and a complex three-dimensional flow field. Past work has been limited to qualitative visualizations such as schlieren imaging, and detailed measurements of the induced flow are required to develop a mechanistic model of the actuator performance. </p><p><br></p><p></p><p>Background-Oriented Schlieren (BOS) is a quantitative variant of schlieren imaging and measures density gradients in a flow field by tracking the apparent distortion of a target dot pattern. The distortion is estimated by cross-correlation, and the density gradients can be integrated spatially to obtain the density field. Owing to the simple setup and ease of use, BOS has been applied widely, and is becoming the preferred density measurement technique. However, there are several unaddressed limitations with potential for improvement, especially for application to complex flow fields such as those induced by plasma actuators. </p><p></p><p>This thesis presents a series of developments aimed at improving the various aspects of the BOS measurement chain to provide an overall improvement in the accuracy, precision, spatial resolution and dynamic range. A brief summary of the contributions are: </p><p>1) a synthetic image generation methodology to perform error and uncertainty analysis for PIV/BOS experiments, </p><p>2) an uncertainty quantification methodology to report local, instantaneous, a-posteriori uncertainty bounds on the density field, by propagating displacement uncertainties through the measurement chain,</p><p>3) an improved displacement uncertainty estimation method using a meta-uncertainty framework whereby uncertainties estimated by different methods are combined based on the sensitivities to image perturbations, </p><p>4) the development of a Weighted Least Squares-based density integration methodology to reduce the sensitivity of the density estimation procedure to measurement noise.</p><p>5) a tracking-based processing algorithm to improve the accuracy, precision and spatial resolution of the measurements, </p><p>6) a theoretical model of the measurement process to demonstrate the effect of density gradients on the position uncertainty, and an uncertainty quantification methodology for tracking-based BOS,</p><p>Then the improvements to BOS are applied to perform a detailed characterization of the flow induced by a filamentary surface plasma discharge to develop a reduced-order model for the length and time scales of the induced flow. The measurements show that the induced flow consists of a hot gas kernel filled with vorticity in a vortex ring that expands and cools over time. A reduced-order model is developed to describe the induced flow and applying the model to the experimental data reveals that the vortex ring's properties govern the time scale associated with the kernel dynamics. The model predictions for the actuator-induced flow length and time scales can guide the choice of filament spacing and pulse frequencies for practical multi-pulse ns-SDBD configurations.</p>

Sootblowing is a process in which supersonic steam jets are used to periodically blast deposits off heat transfer tubes in kraft recovery boilers. However, sootblowing significantly consumes the valuable high pressure steam generated by the boiler, hence it should be optimized. A recovery boiler consists of three convective sections - superheater, generating bank and economizer. The tube arrangement in these sections, particularly the tube spacing is different from each other. Moreover, tubes in an economizer are finned. A sootblower jet will interact differently with these tube arrangements, potentially affecting its strength, and hence deposit removal capability. The objective of this work was to characterize jet/tube interaction in the three sections of a recovery boiler. Lab-scale experiments were conducted in which these interactions were visualized using the schlieren technique coupled with high-speed video, and were quantified by pitot pressure measurements. This work is the first to visualize the interactions. The offset between the jet and tube centrelines, the nozzle exit diameter relative to the tube diameter, and the distance between the nozzle and tube were varied to examine their effects on jet/tube interaction. Results showed that due to the very low spreading rate of a supersonic jet, a jet (primary jet) stops interacting with a superheater platen when the jet is only a small distance away from it. When the jet impinges on a tube, the jet deflects at an angle, giving rise to a weaker ‘secondary’ jet. Due to the large inter-platen spacing, a secondary jet has an insignificant impact in a superheater. In a generating bank, the primary jet weakens between the closely spaced tubes due to increased mixing. However, a secondary jet impinges on the adjacent tubes exerting a high impact pressure on those tubes. The primary jet also weakens between finned economizer tubes, but remains stronger for a greater distance than in a generating bank. As in the case inside a generating bank, a secondary jet also impinges on adjacent rows of tubes in an economizer. The results imply that in a superheater, a sootblower jet must be directed close to the platens to yield useful jet/deposit interactions, and to avoid wasting steam by blowing between the platens. In a generating bank, deposits beyond the first few tubes of a row experience a weaker sootblower jet, and thus may not be removed effectively. However, secondary jets may contribute to removing deposits from the first few adjacent tubes. They may also induce erosion-corrosion of those tubes. Secondary jets may also help remove deposits from adjacent rows in a finned tube economizer. In an economizer, the strength and hence, the deposit removal capability of a sootblower jet diminish only slightly beyond the supersonic portion of the jet. A mathematical model was also developed to determine the feasibility of using inclined sootblower nozzles in recovery boiler superheaters, and suggests that it may be possible to clean superheater platens more effectively with slightly inclined nozzles.

Sootblowing is a process in which supersonic steam jets are used to periodically blast deposits off heat transfer tubes in kraft recovery boilers. However, sootblowing significantly consumes the valuable high pressure steam generated by the boiler, hence it should be optimized. A recovery boiler consists of three convective sections - superheater, generating bank and economizer. The tube arrangement in these sections, particularly the tube spacing is different from each other. Moreover, tubes in an economizer are finned. A sootblower jet will interact differently with these tube arrangements, potentially affecting its strength, and hence deposit removal capability. The objective of this work was to characterize jet/tube interaction in the three sections of a recovery boiler. Lab-scale experiments were conducted in which these interactions were visualized using the schlieren technique coupled with high-speed video, and were quantified by pitot pressure measurements. This work is the first to visualize the interactions. The offset between the jet and tube centrelines, the nozzle exit diameter relative to the tube diameter, and the distance between the nozzle and tube were varied to examine their effects on jet/tube interaction. Results showed that due to the very low spreading rate of a supersonic jet, a jet (primary jet) stops interacting with a superheater platen when the jet is only a small distance away from it. When the jet impinges on a tube, the jet deflects at an angle, giving rise to a weaker ‘secondary’ jet. Due to the large inter-platen spacing, a secondary jet has an insignificant impact in a superheater. In a generating bank, the primary jet weakens between the closely spaced tubes due to increased mixing. However, a secondary jet impinges on the adjacent tubes exerting a high impact pressure on those tubes. The primary jet also weakens between finned economizer tubes, but remains stronger for a greater distance than in a generating bank. As in the case inside a generating bank, a secondary jet also impinges on adjacent rows of tubes in an economizer. The results imply that in a superheater, a sootblower jet must be directed close to the platens to yield useful jet/deposit interactions, and to avoid wasting steam by blowing between the platens. In a generating bank, deposits beyond the first few tubes of a row experience a weaker sootblower jet, and thus may not be removed effectively. However, secondary jets may contribute to removing deposits from the first few adjacent tubes. They may also induce erosion-corrosion of those tubes. Secondary jets may also help remove deposits from adjacent rows in a finned tube economizer. In an economizer, the strength and hence, the deposit removal capability of a sootblower jet diminish only slightly beyond the supersonic portion of the jet. A mathematical model was also developed to determine the feasibility of using inclined sootblower nozzles in recovery boiler superheaters, and suggests that it may be possible to clean superheater platens more effectively with slightly inclined nozzles.

L'objectif de la thèse consiste en l'étude expérimentale du rôle de la température sur le rayonnement acoustique des jets supersoniques.<br />Dans une première étude, on analyse de façon globale les effets de la température sur le bruit de cinq jets ayant des vitesses de jet parfaitement détendu identiques pour des températures différentes (niveau de puissance acoustique global, directivité et analyse spectrale). On examine ainsi les contributions acoustiques des diverses sources sonores en fonction de la température du jet. L'influence de celle-ci sur l'efficacité de la technique d'injection d'eau comme moyen de réduction sonore est par ailleurs étudiée sur ces jets.<br />On s'intéresse ensuite aux valeurs de températures moyennes et fluctuantes locales dans ce type de jets. Pour cela, on développe la méthode optique Schlieren basée sur des mesures de déviations angulaires de faisceaux lumineux à travers l'écoulement et permettant la mesure d'indices de réfraction. La température est obtenue à partir de l'inversion d'une équation intégrale type Abel, de la relation de Gladstone et de la relation d'état des gaz parfaits. Les températures quadratiques sont quant à elles estimées à l'aide de calculs statistiques sur les déviations angulaires mesurées. Cette méthode est dans un premier temps validée sur un écoulement subsonique pour lequel les mesures issues de la méthode optique sont comparées à celles obtenues avec un thermocouple. La méthode Schlieren est finalement appliquée sur les cinq jets dont les conditions sont proches de celles présentes sur les lanceurs spatiaux. Dans le cas du jet parfaitement détendu, les résultats ainsi obtenus sont comparés à des calculs numériques.

<p>Hypersonic flow conditions, such as temperature, pressure, and flow velocity, are challenging to measure on account of the extreme conditions experienced by a craft moving above Mach 5. At Mach 5, the temperature in stratospheric air behind a normal shock wave exceeds temperatures of 1,300 K, and as the craft speed increases, so does the temperature. At these temperatures and conditions, traditional measurement techniques such as thermocouples and pressure transducers either alter the flow path, affecting the measurement, or they do not survive the external conditions. As such, there is interest in investigating alternative ways to measure flow properties. This thesis focuses on the implementation of several optical measurement techniques designed to determine the flow temperature, density gradient, and flow velocity in a detonation driven shock tube. A detonation driven shock tube was chosen for the project as it reliably creates high-speed, low-density, gas flows that are reminiscent of hypersonic conditions. </p><p>The first optical measurement technique implemented was background oriented schlieren, a measurement technique that quantitatively provides density gradient data. Experimental data obtained at pressures up to 3,000 psia resulted in density gradients at the exit of the detonation tube in good agreement with the literature.</p><p>The detonation tube was also fitted with two fiber optic ports to gather chemiluminescence thermometry data. Both a Stellarnet Black-Comet spectrometer and a Sydor Ross 2000 streak camera were used to capture spectroscopic data at these ports, in order to determine the detonation speed and the rotational temperature of the intermediate OH* combustion products. The Stellarnet spectrometer did not have a fast enough data capture rate to gather reliable data. While the streak camera captured data quickly, we had difficulty gathering enough light from the combustion event and the gathered data was very noisy. The streak camera did however capture the time duration of the full combustion event, so if the fiber connector ports are improved this data taking method could be used in the future to gather rotational temperature data. Both measurement techniques provided some unintrusive measurements of high-speed flows, and improvements to the data taking system could provide much needed information on hypersonic flow conditions. </p>

<p>The aerodynamics of insect flight is not well understood despite it has been extensively investigated with various techniques and methods. Its complexities mainly have two folds: complex flow behavior and intricate wing morphology. The complex flow behavior in insect flight are resulted from flow unsteadiness and three-dimensional effects. However, most of the experimental studies on insect flight were performed with 2D flow measurement techniques whereas the 3D flow measurement techniques are still under developing. Even with the most advanced 3D flow measurement techniques, it is still impossible to measure the flow field closed to the wings and body. On the other hand, the intricate wing morphology complicates the experimental studies with mechanical flapping wings and make mechanical models difficult to mimic the flapping wing motion of insects. Therefore, to understand the authentic flow phenomena and associated aerodynamics of insect flight, it is inevitable to study the actual flying insects. </p> <p>In this thesis, a recently introduced technique of schlieren photography is first tested on free jet of match rockets with a physics based optical flow method to explore its potential of flow quantification of unsteady flow. Then the schlieren photography and optical flow method are adapted to tethered and feely flying houseflies to investigate the complex wake flow and structures. In the end, a particle tracking velocimetry system: Shake the Box system, is utilized to resolve the complex wake flow on a tethered house fly and to acquire some preliminary 3D flow field data</p>

Pour répondre aux défis environnementaux actuels, des solutions en rupture par rapport aux turbomachines existantes sont actuellement encours de développement. Elles s’appuient sur des cycles thermodynamiques plus efficients.L’objectif de ces travaux de thèse est d’étudier expérimentalement les mécanismes de transition de régime de combustion pour ce type d'applications en utilisant un surrogate de kérosène, le n-décane. Pour cela, une déflagration est initiée dans une enceinte fermée et comprime les gaz frais. La pression et la température de ces derniers augmentent jusqu’à atteindre les conditions propices à l’apparition de l’autoinflammation.3 régimes de combustion successifs sont caractérisés dans la chambre de combustion au moyen de diagnostics optiques rapides. Un premier dégagement de chaleur associé à la flamme froide pré-oxyde les gaz frais, il est suivi du dégagement de chaleur principal (Main Heat Release,MHR). Pour les températures initiales de mélange les plus élevées, une détonation est observée à la fin du processus. Deux chemins de transition différents sont mis en évidence : la transition Déflagration-Auto-inflammation (DAIT) et la transition Déflagration-Auto-inflammation-Détonation (DAIDT). La sensibilité des transitions de régime aux conditions initiales de pression, de température et de richesse a été caractérisée au moyen de plusieurs études paramétriques. Dans ce but, les conditions de température, de pression et de composition du mélange sont calculées aux instants d’apparition des différents fronts réactifs (flamme froide, MHR et détonation). Il a notamment été observé que les dégagements de chaleur successifs de l’auto-inflammation se déroulaient aux mêmes températures (740 K pour la flamme froide et 1050 K pour le MHR)quelles que soient les conditions initiales. L’étude s’est concentrée ensuite sur l’analyse d’un point de fonctionnement particulier. L’étude de ce point de fonctionnement, différents vitesses de front d’auto-inflammation ont été observées, mettant en évidence le mécanisme de SWACER lors de la transition.Un critère de transition de régime depuis l’auto-inflammation proposé de Zander et al., dans le cadre d’études numériques, a été testé dans notre configuration expérimentale. Un critère modifié a été développé en lui adjoignant la notion d’effets de compressibilité dans l’écoulement réactif. L’application de ce critère à l’ensemble des essais permet de prédire l’apparition de la détonation dans les conditions où 0 et 100 % de DAIDT sont observés. Les différents domaines de transition de régime ont également été positionnés sur le diagramme de Bradley (ξ, ϵ). Les modes de combustion prédits par le diagramme sont consistants avec ceux qui sont atteints dans la chambre.L’influence de la distribution initiale de température sur les modes de combustion atteignables dans la chambre a été étudiée. Trois topologies d’auto-inflammation ont été mises en évidence pour trois distributions de température dans la chambre. Ces topologies sont séparées en deux catégories, celles privilégiant une direction particulière lors de l’auto-inflammation séquentielle et celle présentant un comportement tridimensionnel.Les essais ayant un comportement tridimensionnel présentent une très forte propension à la DAIDT mais une propagation lente des fronts d’auto-inflammation. Dans ce cas, un autre mécanisme de transition vers la détonation est mis en évidence : l’auto-inflammation d’une poche homogène de gaz génère des ondes de choc et déclenchent des auto-inflammations successives pendant leur propagation. Le couplage choc/front réactif entraine la formation de la détonation.Différents mécanismes de transition vers la détonation ont été observés et étudiés sur une large plage de conditions de pression, température,richesse et gradient thermique. Les résultats obtenus permettront d’appuyer les études numériques réalisées sur le sujet, manquant jusque-là de données expérimentales en conditions académiques. / To meet the current environmental challenges, breakthrough solutions compared to existing turbomachines are currently under development.They rely on the use of more efficient thermodynamic cycles.The objective of this thesis is to study experimentally the mechanisms of transition of combustion regime using a kerosene surrogate, n-decane.For this purpose, a deflagration is initiated in a closed chamber and compresses the fresh gases. The pressure and the temperature of the endgas increase until reaching the conditions favorable to the appearance of the autoignition in the chamber.3 successive combustion regimes are characterized in the combustion chamber by means of fast optical diagnostics. A first heat release,associated with the cool flame phenomenon, pre-oxidizes the fresh gases, it is followed by the Main Heat Release (MHR). For the highest initial temperatures, a detonation is observed at the end of the process. Two different transition paths are highlighted: the Deflagration-Autoignition Transition (DAIT) and the Deflagration-Autoignition-Detonation Transition (DAIDT).The sensitivity of regime transitions to the initial conditions of pressure, temperature and mixture composition was characterized by means of several parametric studies. For this purpose, the conditions of temperature, pressure and composition of the mixture are calculated at the onset of the different reactive fronts (cool flame, MHR and detonation). In particular, it has been observed that the successive heat releases of theauto-ignition start at the same temperatures (740 K for the cool flame and 1050 K for the MHR) whatever the initial conditions. The study, then, focused on the analysis of a particular operating point. During the study of this operating point different self-ignition front velocities were observed, highlighting the mechanism of SWACER during the transition.A regime transition criterion proposed by Zander et al. based on numerical studies has been tested in our experimental setup. A modified criterion has been developed to take into account compressibility effects in the reactive flow. The application of this criterion to all the dataset makes possible to predict the appearance of the detonation under the conditions where 0 and 100% of DAIDT are observed. The different regime transition domains have also been positioned on the Bradley diagram (ξ, ε). The modes of combustion predicted by the diagram are consistent with those reached in the chamber.The influence of the initial temperature distribution on the combustion modes achievable in the chamber has been studied. Three topologies of autoignition have been demonstrated for three initial temperature distributions in the chamber. These topologies are separated into two categories, those favoring a particular direction during sequential self-ignition and that exhibiting a three-dimensional behavior.Three-dimensional tests show a very high propensity for DAIDT but a slow spread of autoignition fronts. In this case, another mechanism of transition to detonation is evidenced: the self-ignition of an homogeneous gas pocket generates shock waves and triggers successive autoinflammations during their propagation. The shock coupling / reactive front causes the formation of the detonation. Different transition mechanisms to detonation have been observed and studied over a wide range of pressure, temperature, equivalence ratio and thermal gradient conditions. The obtained results will be useful to support the numerical studies carried out on the subject, which lacks experimental data in academic conditions.