The motion of shock waves is important in many fields of engineering and increasingly so with medical applications and applications to inertial confinement fusion technologies. The flow structures that moving shock waves create when they encounter a change in area is complex and can be difficult to understand. Previousresearchers have carried out experimental studies and many numerical studies looking at this problem in more detail. There has been a discrepancy between numerical and experimental work which had remained unanswered. One of the aims of this project is to try and resolve the discrepancy between numerical and experimental work and try to investigate what experimental techniques are suitable for work of this type and the exact way in which they should be applied. Most previous work has focused on sharp changes in geometry which induce immediate flow separation. In this project rounded corners will also be investigated and the complex flow features will be analyzed.Two geometries, namely a sharp 172 degree knife-edge and a 2.8 mm radius rounded corner will be investigated at three experimental pressure ratios of 4, 8 and 12 using air as the driver gas. This yields experimental shock Mach numbers of 1.28, 1.46 and 1.55. High-speed schlieren and shadowgraph photography with varying levels of sensitivity were used to qualitatively investigate the wave structures. Particle image velocimetry (PIV), pressure-sensitive paint (PSP) and traditional pressure transducers were used to quantify the flow field. Numerical simulations were performed using the commercial package Fluent to investigate the effect of numerical schemes on the flow field produced and for comparison with the experimental results. The sharp geometry was simulated successfully using an inviscid simulation while the rounded geometry required the addition of laminar viscosity. Reynolds number effects will be only sparsely referred to in this project as the flows under investigation show largely inviscid characteristics. As the flow is developing in time rather than in space, quotation of a distance-based Reynolds number is not entirely appropriate; however, Reynolds number based on the same spatial location but varying in time will be mentioned. The density-based diagnostics in this project were designed to have a depth of field appropriate to the test under consideration. This approach has been used relatively few times despite its easy setup and significant impact on the results. This project contains the first quantative use of PIV and PSP to shock wave diffraction. Previous studies have almost exclusively used density-based diagnostics which, although give the best impression of the flow field, do not allow for complete analysis and explanation of all of the flow features present. PIV measurements showed a maximum uncertainty of 5% while the PSP measurements showed an uncertainty of approximately 10%.The shock wave diffraction process, vortex formation, shear layer structure, secondary and even tertiary expansions and the shock vortex interaction were investigate. The experimental results have shown that using one experimental technique in isolation can give misleading results. Only by using a combination of experimental techniques can we achieve a complete understanding of the flow field and draw conclusions on the validity of the numerical results. Expanding the range of the experimental techniques currently in use is vital for experimental aerodynamic testing to remain relevant in an industry increasingly dominated by numerical research. To this end, significant research work has been carried out on extending the range of the PSP technique to allow for the capture of shock wave diffraction, one of the fastest transient fluid processes, and for applications to low-speed flow (< 20 ms−1).

La miniaturisation de plus en plus poussée (micro et nano) des systèmes mécanique connaît un important développement depuis une dizaine d'années. Leur conception et réalisation nécessite une connaissance approfondie des écoulements micro-fluidiques. Dans le domaine énergétique, le rendement d'un moteur thermique se dégrade sérieusement lors d'une réduction d'échelle. En effet, les pertes de chaleur pariétales peuvent devenir aussi importantes que l'énergie libérée. Une voie prometteuse consiste à utiliser les ondes de choc / détonation pour accélérer la libération d'énergie. Dans ce cas, la détonation peut être assimilée à une onde de choc inerte, couplée à une zone de réaction, caractérisée par la présence d'instabilités longitudinales et transverses, soumettant ainsi le front de choc à de violentes accélérations / décélérations. L'objectif de la thèse est de mieux appréhender la structure moyenne de la zone de réaction qui s'étend du choc jusqu'à la surface sonique. Sur le plan de la modélisation numérique, les équations de Navier-Stokes compressibles, multi-espèces, réactives sont résolues au sein du solveur CHOC-WAVES développé au CORIA, avec une thermodynamique variables et des coefficients de transport dépendant des espèces. La condition de Chapman-Jouguet généralisée a été élaborée et confirmée par les résultats de simulations numériques dans le cas d'une détonation multidimensionnelle stable. En particulier, il a été montré que les instabilités transverses s'atténuaient avec la réduction d'échelle. A cet effet, un scénario a été proposé pour expliquer le déficit de la vitesse du front de détonation, en se basant sur la structure de la poche subsonique aval, en corrélation avec l'épanouissement de la couche limite. Ce schéma partage de fortes similitudes avec la macro-détonation, tout en gardant des différences. En particulier, il a été montré que la forte vorticité, produite au niveau de la singularité de Prandtl-Meyer, souvent négligée dans les modèles de macro-détonation, diffusait au sein de la poche subsonique. Ces résultats tout à fait originaux ont permis une avancée significative dans la compréhension du mécanisme de propagation des fronts de détonation stables et confinées. / Progress towards the miniaturization of increasingly advanced micro- and nano-electromechanical systems has highlighted the need for a better knowledge of the design of such devices. knowledge of micro-nano pipe flows is still mandatory. In field of energy power generation, as the systems are scaled down, the thermal efficiency of conventional propellant devices is seriously degraded due to significant heat losses which can cause the combustion extinction. A promising approach is to use shock or detonation waves in gazeous media to enhance chemical reaction rates. A detonation is a rapid regime of burning in which a strong shock ignites the fuel and the burning proceeds to equlibrium behind the shock, while the energy released continues to drive the shock. It is also characterized by the presence of longitudinal and transverse instabilities, thereby subjecting the shock front to violent deceleration / acceleration. The objective of this thesis is to better understand the mean structure of the reaction zone that extends from the shock to the sonic surface. As for numerical modelling, the compressible multi-species reactive Navier-Stokes equations are solved using an in-house code "CHOC-WAVES", including variable thermodynamic and transport coefficients depending on the species. The Generalized Chapman-Jouguet condition was developed and corroborated by the numerical results in the case of stable multidimensionnal detonation. More specially, it was shown that the transverse instabilities are attenuated with the scale reduction.To this end, a scenarion, based on the structure of downstream subsonic pocket, which is correlated to the development of the boundary layer, has been proposed to explain the deificit of the detonation from velocity. This scheme shares many similarities with the macro-detonation, while keeping some differences. In particular, it was shown that the strong vorticity, generated at the Prandlt-Meyersingularity and often neglected in macro-detonation models, diffuses in the subsonic pocket. The present contribution enables us to shade more physical insight for the propagation of stable and confined detonation fronts.

<p>&nbsp;U okviru ove doktorske disertacije posmatrani su zakoni održanja sa funkcijom fluksa koja ima prekid u x = 0, pri čemu delovi fluksa levo i desno od x = 0 imaju smo po jedan ekstrem. U prvoj glavi se može naći pregled osnovnih pojmova, definicija i teorema. U drugoj&nbsp; glavi su opisani hiperbolični sistemi zakona održanja, slaba re&scaron;enja, kao&nbsp;<br />i numerički postupci za njihovo re&scaron;avanje. U trećoj glavi su predstavljeni&nbsp; diskretni profili darnih talasa. U četvrtoj glavi su opisani zakoni održanja&nbsp; sa prekidnom funkcijom fluksa i ukratko su predstvaljeni rezultati drugih autora iz ove oblasti. U petoj glavi je najpre analizirana tzv. jednačina sa dva fluksa u slučaju kada oba dela fluksa levo i desno od&nbsp; x = 0 imaju minimum, a pri tome se seku u najvi&scaron;e jednoj tačci unutar intervala. Primenom regularizacije na intervalu [&minus;<em>&epsilon;, &epsilon;</em>], za<em> &epsilon;</em> &gt; 0 dovoljno malo, dokazano je postojanje diskretnih udarnih profila za postupak Godunova za zakone održanja sa promenljivom funkcijom fluksa. Definisan je i odgovarajući diskretan uslov entropije, a postojanje entropijskog diskretnog&nbsp; udarnog profila je postavljen kao kriterijum za dopustivost udarnih talasa. Potom je analizirana ista jednačina u slucaju kada deo fluksa levo&nbsp; od x = 0 ima maksimum, a deo fluksa desno od x = 0 minimum, dok se oba dela fluksa seku na&nbsp; krajevima posmatranog intervala. U ovom slučaju, uop&scaron;ten je uslov entropije. U okviru ove glave je prikazano nekoliko numeričkih primera za oba opisana slučaja. Numerički rezultati&nbsp; su dobijeni kori&scaron;cenjem softvera razvijenog za potrebe ove teze u pro<br />gramskom paketu <em>Mathematica</em>.</p> / <p>We consider conservation laws with a flux discontinuity at x = 0, where the flux parts from both left and right hand side of x = 0 have at most one extreme on the&nbsp; observed &nbsp;domain. The first chapter provides elementary definitions and theorems..The second chapter refers to hyperbolic systems of conservation laws, their solutions, and&nbsp; numerical procedures. The third chapter is devoted to discrete&nbsp; shock profiles. The fourth chapter describes conservation laws with discontinuous flux functions and provides basic information upon known results in this field. In the&nbsp; fifth chapter, we first &nbsp;analyse the two-flux equation when both flux parts have a minimum and cross at most&nbsp;&nbsp;&nbsp; at one point in the interior of the domain. Using a flux regularization on the interval [&minus;&epsilon;,&nbsp;&nbsp; &epsilon;], for &epsilon; &gt; 0 small enough, we show the existence of discrete shock profiles for Godunov&rsquo;s scheme for conservation laws with discontinuous flux functions. We also define a discrete entropy condition accordingly, and use the existence of an entropy discrete shock profile as an entropy criterion for shocks. Then we analyse the same problem in the case when the flux part on the left of x = 0 has a maximum and the part on the right of x = 0 has a minimum, whereas the fluxes cross at the edges of the interval. We derive a more general discrete entropy condition in this case. We provide several numerical examples in both of the above mentioned flux cases. All the&nbsp; presented numerical results are obtained using a program written in Mathematica. Finally, in chapter six, we prove the existence of&nbsp; singular shock waves in the case when the graph of one of the flux parts is above the graph of the other one on the entire domain. For that purpose, we use the shadow wave technique. At the end of this chapter, we provide a numerical verification of the obtained singular solution.</p>

<div>Shock-wave/turbulent boundary-layer interactions (SWTBLIs) are characterized by low-frequency unsteadiness, amplified aerothermal loads, and a complex three-dimensional flowfield. Presence of a broad range of length and time-scales associated with compressible turbulence generates additional gasdynamic features that interact with different parts of the flowfield via feedback mechanisms. Determining the physics of such flows is of practical importance as they occur frequently in different components of a supersonic/hypersonic aircraft such as inlets operating in both on- and off-design conditions, exhaust nozzles, and control surfaces. SWTBLIs can cause massive flow separation which may trigger unstart by choking the flow in an inlet. On control surfaces, fatigue loading caused by low-frequency shock unsteadiness, coupled with high skin-friction and heat transfer at the surface, can result in failure of the structure.</div><div><br></div><div>The objective of this study is twofold. The first aspect involves examining the causes of unsteadiness in SWTBLIs associated with two geometries – a backward facing step flow reattaching on to a ramp, and a highly confined duct flow. Signal processing and statistical techniques are performed on the results obtained from Delayed Detached-Eddy Simulations (DDES) and Implicit Large-Eddy Simulations (ILES). Dynamic Mode Decomposition (DMD) is used as a complement to this analysis, by obtaining a low-dimensional approximation of the flowfield and associating a discrete frequency value to individual modes. </div><div><br></div><div>In case of the backward facing step, Fourier analysis of wall-pressure data brought out several energy dominant frequency bands such as separation bubble breathing, oscillations of the reattachment shock, shear-layer flapping, and shedding of vortices from the recirculation zone. The spectra of reattachment shock motion suggested a broadband nature of the oscillations, wherein separation bubble breathing affected the low-frequency motion and shear-layer flapping, and vortex shedding correlated well at higher frequencies. A similar exercise was carried out on the highly confined duct flow which featured separation on the floor and sidewalls. In addition to the low-frequency shock motions, the entire interaction exhibited a cohesive back-and-forth in the streamwise direction as well as a left-right motion along the span. Mode reconstruction using DMD was used in this case to recover complex secondary flows induced by the presence of sidewalls.</div><div><br></div><div>For the final aspect of this study, a flow-control actuator was computationally modeled as a sinusoidally varying body-force function. Effects of high-frequency forcing at F⁺ =1.6 on the flowfield corresponding to a backward facing step flow reattaching on to a ramp were examined. Conditionally averaged profile of streamwise velocity fluctuations, based on reattachment shock position, was used for the formulation of spatial distribution of the actuator. The forcing did not change the mean and RMS profiles significantly, but affected the unsteadiness of the interaction significantly. The effects of forcing were localized to the recirculation zone and did not affect the evolution of the shear-layer. The acoustic disturbances propagating through the freestream and recirculation zone drove the motion of the reattachment shock, and did not alter the low-frequency dynamics of the interaction.</div>

<p>U doktorskoj disertaciji posmatrani su Rimanovi problemi kod strogo i slabo hiperboličnih&nbsp;nelinearnih sistema PDJ. U uvodu je predstavljena jednačina zakona održanja u jednoj prostornoj&nbsp;dimenziji i definisani su Ko&scaron;ijevi i Rimanovi problemi. U drugoj glavi, date su osnovne osobine&nbsp;nelinearnih hiperboličnih zakona održanja, uvedeni supojmovi stroge hiperboličnosti i slabog re&scaron;enja&nbsp;zakona održanja. Definisani su Rankin-Igono i entropijski uslovi kao i op&scaron;te re&scaron;enje Rimanovog problema&nbsp;(za dovoljno male početne uslove). U trećoj glavi detaljno je obja&scaron;njena Glimova diferencna &nbsp;&scaron;ema. Metod&nbsp;praćenja talasa predstavljen je u četvrtoj glavi. Pokazano je da se ovom metodom, za dovoljno male&nbsp;početne uslove, dobija stabilno i jedinstveno re&scaron;enje koje u svakom vremenu ima ograničenu totalnu&nbsp;varijaciju. U petoj glavi, posmatrana je jednačina protoka izentropnog gasa u Lagranžovim koordinatama.&nbsp;Uz pretpostavku da je početni uslov ograničen i da ima ograničenu totalnu varijaciju, pokazano je da&nbsp;Ko&scaron;ijev problem ima jedinstveno slabo re&scaron;enje ako je totalna varijacija početnog uslova pomnožena sa &nbsp;0&lt;&epsilon;&lt;&lt; 1 dovoljno mala. Slabo re&scaron;enjedobijeno je metodom praćenja talasa. U glavi &scaron;est ispitana je&nbsp;interakcija dva delta talasa koji su posmatrani kao specijalna vrsta shadowtalasa. U glavi sedam,&nbsp;pokazano je da za proizvoljno velike početne uslove, re&scaron;enje Rimanovog problema jednodimenzionalnog&nbsp;Ojlerovog zakona održanja gasne dinamikepostoji, daje jedinstveno i entropijski dopustivo, uz drugačiju<br />ocenu snaga elementarnih talasa. Data je numerička verifikacija interakcije dva delta talasa kori&scaron;ćenjem&nbsp;metode praćenja talasa.</p> / <p>In this doctoral thesis, Riemann problems for strictly and weakly nonlinear hyperbolic PDE&nbsp;systems were observed. In the introduction, conservation laws in one spatial dimension were presented&nbsp;and the Cauchy and Riemann problems were defined. In the second chapter, the basic properties of&nbsp;nonlinear hyperbolic conservation laws were intorduced, as well as the terms such as strictly hyperbolic&nbsp;system and weak solution of conservation law. Also, Rankine -Hugoniot and entropy conditions were<br />introduced and the general solution to the Riemann problem (for sufficiently small initial conditions) were&nbsp;defined. Glimm&rsquo;s difference scheme was explained in the third chapter. The wave front tracking method&nbsp;was introduced in the fourth chapter. It was shown that, using this method, for sufficiently small initial&nbsp;conditions, it could be obtained a unique solution with bounded total variation for t &ge;0. In the fifth&nbsp;chapter, the Euler equations for isentropic fluid inLagrangian coordinates were observed. Under the&nbsp;assumption that the initial condition was bounded and had bounded total variation, it was shown that the&nbsp;Cauchy problem had a weak unique solution, provided that the total variation of initial condition&nbsp;multiplied by 0&lt;&epsilon;&lt;&lt;1 was sufficiently &nbsp;small. Weak solution was obtained by applying the wave front&nbsp;tracking method. In the sixth chapter, the interaction of two delta shock waves were examined. Delta&nbsp;shock waves were regarded as special kind of shadowwaves. In the chapter seven, it was shown that for&nbsp;arbitrarily large initial conditions, solution to the Riemann problem of one-dimensional Euler&nbsp;conservation laws of gas dynamics existed, it was unique and admissible. New bounds on the strength of&nbsp;elementary waves in the wave front tracking algorithm were given. The numerical verification of two&nbsp;delta shock waves interaction via wave front tracking method was given at the end of the thesis.</p>

No description available.

[ES] En los turbocompresores con turbina de geometría variable (VGT por sus siglas en inglés) los vanos del estator se mueven a una posición cerrada para generar una contrapresión durante el modo de frenado del motor. De este modo, se generan ondas de choque en el estator. Además, en otras aplicaciones donde se utilizan turbinas radiales como en ciclos reversos de Brayton para refrigeración, ciclos orgánicos Rankine, y en las turbinas para la unidad de potencia auxiliar, dependiendo de las condiciones de operación, pueden aparecer condiciones sónicas y ondas de choque. El presente trabajo se centra en el estudio del comportamiento del flujo a través de una turbina de geometría variable de un turbocompresor comercial en condiciones fuera de diseño alcanzando condiciones de choque. Se ha realizado un análisis detallado del patrón de flujo dentro de la turbine usando simulaciones CFD, identificando y cuantificando los fenómenos más importantes bajo diferentes condiciones de operación. Se han llevado a cabo simulaciones estacionarias usando Reynolds Averaged Navier Stokes (RANS) y no estacionarias (unsteady RANS) para obtener las características del flujo en el estator y en el rotor, además de obtener el mapa de la turbina. Los resultados CFD muestran que la región del dominio computacional donde aparecen las condiciones sónicas depende de la posición de los vanos del estator y la relación de presiones. Cuando los vanos del estator están en una posición cerrada (10% VGT), el fluido se acelera y, dependiendo de la relación de presiones, la presión estática en el lado de succión disminuye hasta cierto punto donde un incremento repentino revela la presencia de una onda de choque, la cual se expande por el espacio sin vanos. La intensidad de la onda de choque bajo la relación de presiones más altas varia con la velocidad de giro. Para analizar la interacción entre el rotor y el estator se llevaron a cabo simulaciones numéricas con los vanos del estator en una posición cerrada, 10% VGT, y en una posición más abierta, 30% VGT. El número de choques que una partícula del fluido experimenta aguas arriba del rotor está correlacionado con las pérdidas por choque del fluido. Cerca de los vanos del estator, las pérdidas de presión son altas, hacia el centro del espacio sin vanos las pérdidas disminuyen y cerca del rotor empiezan a incrementar. La interacción entre el rotor y el estator crea ondas de choque cuya intensidad depende de la posición del borde de ataque del rotor y de la velocidad de giro. A la velocidad de giro más alta, ocurren fluctuaciones en la carga cerca del borde de ataque, las cuales pueden comprometer la integridad de la pala. Cuando la turbina tiene los vanos del estator abiertos (80% VGT) y opera a la relación de presión más alta seleccionada, las condiciones de choque aparecen en el plano del borde de fuga del rotor. Además, el desarrollo del área chocada depende de la velocidad de giro y de las fugas en la punta del álabe. Así, se investigó los efectos de las fugas en la punta del alabe sobre el flujo principal bajo condiciones sónicas disminuyendo e incrementando el intersticio entre la punta del álabe y la carcasa hasta un 50% en base a la geometría dada por el fabricante. El flujo a través de este espacio se acelera para posteriormente mezclarse con el flujo principal y generar un vórtice. Los efectos del vórtice sobre el flujo en el plano ubicado en el borde de fuga del rotor cuando el intersticio varía son más significativos a altas velocidades que a bajas velocidades. El vórtice permanece más cerca del lado de succión a altas velocidades generando una región subsónica que incrementa con la altura del intersticio. Las fugas en la punta del álabe no afectan al flujo principal cerca del cubo cuando la turbina opera a altas y bajas velocidades. / [CA] En turbocompressors amb turbina de geometria variable (VGT per les seues sigles en anglès), les paletes de l'estàtor es mouen a una posició tancada per generar una contrapressió durant el mode de frenada del motor. D'aquesta forma, es generen unes ones de xoc en l'estàtor. A més, en altres aplicacions on s'utilitzen turbines radials com els cicles inversos de Brayton per a refrigeració, cicles orgànics de Rankine o en turbines per a la unitat de potencia auxiliar, depenent de les condicions d'operació poden aparéixer condicions sòniques i d'ones de xoc. El present treball es centra en l'estudi del comportament del flux en una turbina radial de geometria variable d'un turbocompressor comercial en condicions fora de disseny, arribant a condicions de xoc. S'ha realitzat un anàlisi detallat del patró de flux dins d'aquestes turbines utilitzant simulacions CFD, identificant i quantificant els fenòmens més importants a diferents condicions d'operació. S'han realitzat simulacions estacionàries utilitzant Reynolds Averaged Navier Stokes (RANS) i no estacionàries (Unsteady-RANS) per a obtenir les característiques del flux en l'estàtor i en el rotor, a més d'obtenir el mapa de la turbina. Els resultats CFD mostren que la regió del domini computacional on apareixen les condicions sòniques depenen de la posició de les paletes de l'estàtor i de la relació de pressions. Quan les paletes de l'estàtor estan en una posició tancada (10% VGT), el flux s'accelera i, depenent de la relació de pressions, la pressió estàtica en el costat de succió disminueix fins a cert punt on un increment brusc denota la presència d'una ona de xoc que s'expandix per l'espai sense paletes. L'intensitat de la ona de xoc a relacions de pressions elevades varia amb la velocitat de rotació. Per analitzar l'interacció entre rotor i estàtor es van realitzar simulacions numèriques amb les paletes de l'estàtor en una posició tancada, 10% VGT, i en una posició més oberta, 30% VGT. El nombre de xocs que una partícula del fluid experimenta aigües amunt del rotor està correlacionat amb les pèrdues per xoc del fluid. Prop de les paletes de l'estàtor, les pèrdues de pressión són elevades, cap al centre de l'espai sense paletes les pèrdues disminueixen i prop del rotor comencen a incrementarse. L'interacción entre rotor i estàtor crea ones de xoc amb una intensitat que depèn de la posició de la vora d'atac del rotor i de la velocitat de rotació. A la velocitat de rotació més elevada, prop de de la vora d'atac ocorren fluctuacions en la càrrega que poden comprometre la integritat de la pala. Quan la turbina té les paletes de l'estàtor obertes (80% VGT) i opera a la relació de pressió més elevada de les seleccionades, les condicions de xoc apareixen en el pla de la vora de fuga del rotor. A més, el desenvolupament de l'àrea xocada depèn de la velocitat de rotació i de les fugues en la punta de les paletes. Així, s'ha investigat els efectes de les fugues en la punta de les paletes sobre el flux principal sota condicions sòniques, disminuint i incrementant l'interstici entre la punta de la paleta i la carcasa fins un 50\% en base a la geometria donada pel fabricant. El flux en aquest espai s'accelera per a posteriorment mesclar-se amb el flux principal i generar un vòrtex. Els efectes del vòrtex sobre el flux en el pla ubicat a la vora de fuga del rotor quan l'interstici varia són més significatives a velocitats altes que a velocitats baixes. El vòrtex roman més prop del costat de succió a velocitats elevades generant una regió subsònica que incrementa amb l'altura de l'interstici. Les fugues en la punta de les paletes no afecten al flux principal prop del cub quan la turbina opera tant a altes com baixes velocitats. / [EN] In turbochargers with variable geometry turbine (VGT), the stator vanes move to a closed position to drive high exhaust back pressure during the engine braking mode. Thus, shock waves are generated at the stator. Furthermore, depending on the operational conditions in the use of radial turbines in other applications like reverse Brayton cycle for refrigeration, Organic Rankine Cycles, and gas turbine auxiliary power unit (GTAPU), sonic flow and shock waves can appear. The current work focuses on studying the flow behavior of a commercial turbocharger turbine of variable geometry at off-design conditions reaching choked flow. A detailed examination of the flow patterns within the turbine has been carried out using CFD simulations, identifying and quantifying the most important phenomena under different operational points. Reynolds Averaged Navier Stokes (RANS) and unsteady RANS simulations have been performed to obtain the flow structures in stator and rotor as well as the turbine map. The CFD results show that the region of the computational domain where the sonic conditions appear depends on the stator vanes position and the pressure ratio. When the stator vanes are in the closed position (10% VGT) the flow through the stator accelerates and, depending on pressure ratio, the static pressure on the suction side decreases until a certain point where a sudden increase reveals the presence of a shock wave that expands through the vaneless space. The intensity of the shock wave at higher pressure ratio varies with the rotational speed. To analyze the rotor-stator interaction, numerical simulations were carried out with the stator vanes at the closed position, 10% VGT, and at wider position, 30% VGT. The number of shocks a fluid particle experiences upstream of the rotor is correlated with the fluid shock losses. Close to the stator vanes, the pressure losses are high; toward the center of the vaneless space, they start to decrease, and close to the rotor they start to increase. The rotor-stator interaction creates shock waves, whose intensity depends on the position of the rotor leading edge and the blade speed. At higher rotational speed, load fluctuation occurs close to the leading edge, which may compromise the blade's integrity. When the turbine has the stator vanes open (80% VGT) and operates at the selected higher pressure ratio, the choking condition appears in a plane at the rotor trailing edge. Furthermore, the development of the choked area depends on the rotational speed and tip leakage. Thus, the effect of the tip leakage flow on the main flow under sonic conditions was investigated decreasing and increasing the tip gap up to 50% of the original geometry given by the manufacturer. The flow through the gap accelerates and then mixes with the main flow, generating a vortex. The effects of the vortex on the flow at the rotor trailing edge plane when the tip gap varies are more significant at higher speed than at lower speed. The vortex stays closer to the tip suction side at higher speed, generating a subsonic region that increases with the tip gap height. At higher and lower rotational speeds, the tip leakage flow does not affect the main flow close to the hub. / I would like to acknowledge the financial support received through the "Subprograma de Formación de Profesorado Universitario (FPU)". Ministerio de Universidades. FPU18/02628 and by the "FPI Subprograma 2". Universitat Politècnica de València. PAID-10-18. / Echavarría Olaya, JD. (2023). Numerical Study of a Radial Turbine of Variable Geometry at Off-Design Conditions Reaching Choked Flow [Tesis doctoral]. Universitat Politècnica de València. https://doi.org/10.4995/Thesis/10251/196861

Cette thèse est dédiée à l'étude de l'analogue du rayonnement de Hawking dans les condensats de Bose-Einstein. Le premier chapitre présente de nouvelles configurations d'intérêt expérimental permettant de réaliser l'équivalent acoustique d'un trou noir gravitationnel dans l'écoulement d'un condensat atomique unidimensionnel. Nous donnons dans chaque cas une description analytique du profil de l'écoulement, des fluctuations quantiques associées et du spectre du rayonnement de Hawking. L'analyse des corrélations à deux corps de la densité dans l'espace des positions et des impulsions met en évidence l'émergence de signaux révélant l'effet Hawking dans nos systèmes. En démontrant une règle de somme vérifiée par la matrice densité à deux corps connexe, on montre que les corrélations à longue portée de la densité doivent être associées aux modifications diagonales de la matrice densité à deux corps lorsque l'écoulement du condensat présente un horizon acoustique. Motivés par des études expérimentales récentes de profils d'onde générés dans des condensats de polaritons en microcavité semi-conductrice, nous analysons dans un second chapitre les caractéristiques superfluides et dissipatives de l'écoulement autour d'un obstacle localisé d'un condensat de polaritons unidimensionnel obtenu par pompage incohérent. Nous examinons la réponse du condensat dans la limite des faibles perturbations et au moyen de la théorie de Whitham dans le régime non-linéaire. On identifie un régime dépendant du temps séparant deux types d'écoulement stationnaire et dissipatif : un principalement visqueux à faible vitesse et un autre caractérisé par un rayonnement de Cherenkov d'ondes de densité à grande vitesse. Nous présentons enfin des effets de polarisation obtenus en incluant le spin des polaritons dans la description du condensat et montrons dans le troisième chapitre que des effets similaires en présence d'un horizon acoustique pourraient être utilisés pour démontrer expérimentalement le rayonnement de Hawking dans les condensats de polaritons. / This thesis is devoted to the study of the analogue of Hawking radiation in Bose-Einstein condensates. The first chapter presents new configurations of experimental interest making it possible to realize the acoustic equivalent of a gravitational black hole in the flow of a one-dimensional atomic condensate. In each case we give an analytical description of the flow pattern, the associated quantum fluctuations, and the spectrum of Hawking radiation. Analysis of the two-body density correlations in position and momentum space emphasizes the occurrence of signals revealing the Hawking effect in our systems. By demonstrating a sum rule verified by the connected two-body density matrix we show that the long-range density correlations have to be associated to the diagonal modifications of the two-body density matrix when the flow of the condensate presents an acoustic horizon. Motivated by recent experimental studies of wave patterns generated in semiconductor microcavity polariton condensates we analyze in a second chapter superfluid and dissipative characteristics of the flow of a nonresonantly pumped one-dimensional polariton condensate past a localized obstacle. We examine the response of the condensate in the weak-perturbation limit and by means of Whitham theory in the nonlinear regime. We identify a time-dependent regime separating two types of stationary and dissipative flow: a mostly viscous one at low velocity and another one characterized by Cherenkov radiation of density waves at large velocity. Finally we present polarization effects obtained by including the spin of polaritons in the description of the condensate and show in the third chapter that similar effects in the presence of an acoustic horizon could be used to experimentally demonstrate Hawking radiation in polariton condensates.

Title Comparison between the effectiveness of extracorporeal shockwave therapy (ESWT) and the surgical approach in the treatment of the rotator cuff tendinopathy. Objective The main goal of this research work is comparing the effectiveness of extracorporeal shock wave therapy and the surgical intervention (arthroscopic approach) in the treatment of calcific rotator cuff tendinopathy depending on the outcome measures of the Constant-Murley Score (CMS), and the Visual Analogue Scale (VAS) from the recent scientific publications. Methodology This thesis is systemic (literature) review. The studies which recruited in this research were randomized controlled trials, prospective studies, and retrospective case series studies which written in English language form, and published between the year 2000 to the year 2018. The studies were retrieved from following databases: EMBASE, PubMed, CINAHL, Medline, SpringerLink, ProQuest using different integrations of the key words. The participants in the studies were from both genders and all ages. The type of the pathology which included in this research was chronic calcific rotator cuff tendinopathy. Regarding the intervention types both Radial, and Focused ESWT with low, medium, and high intensities and the arthroscopic interventions were the main types of...

O efeito da terapia por ondas de choque (TOC) na consolidação óssea, após osteotomias bilaterais dos fêmures e osteossínteses com hastes bloqueadas, foi estudado em 8 cães. Os fêmures direitos constituíram o grupo controle e os esquerdos, o grupo tratado, que recebeu 2000 pulsos de ondas de choque de 18 kV, energia de 5mJ (-6dB), na linha da fratura. Radiografias após 4, 8 e 12 semanas, revelaram maior proliferação periosteal no grupo tratado. Os resultados dos exames cintilográficos (razão tratado/controle), realizados na 2a, 4a, 6a, 8a, 10a e 12a semanas, foram estatisticamente superiores no grupo tratado. A TOC provocou aumento da atividade osteogênica na consolidação de fraturas agudas / The effect of extracorporeal shock wave therapy (ESWT) on bone healing, after bilateral femoral osteotomies and osteosynthesis with interlocking nails, was studied in 8 dogs. The right femurs composed the control group, and the left femurs, the treated group, which received 2000 pulses of shock wave, with 18 kV, 5 mJ (-6dB) energy on the fracture line. Radiographs after 4, 8 and 12 weeks, revealed increased periosteal proliferation in the treated group. The results (treated/control ratio) of the scintigraphic exams, performed on weeks 2, 4, 6, 8, 10 and 12, were statistically higher for the treated group. The ESWT led to increased osteogenic activity on acute fracture's bone healing.