Control of vortex-driven instabilities was demonstrated via a scaled-down, cold-flow simulation that modeled closed-end acoustics. When vortex shedding frequencies couple with the natural acoustic modes of a choked chamber, potentially damaging low-frequency instabilities may arise. Although passive solutions can be effective, an active control solution is preferable. An experiment was performed to demonstrate an active control scheme for the reduction of vortex-driven oscillations. A non-reacting experiment using a primary flow of air, where both the duct exit and inlet are choked, simulated the closed-end acoustics. Two plates, separated by 1.27 cm, produced the vortex shedding phenomenon at the chamber's first longitudinal mode. Two active control schemes, closed-loop and open-loop, were studied via a cold-flow simulation for validating the effects of reducing vortex shedding instabilities in the system. Actuation for both control schemes was produced by using a secondary injection method. The actuation system consisted of pulsing compressed air from a modifed, 2-stroke model airplane engine, controlled and powered by a DC motor. The use of open-loop only active control was not highly effective in reducing the amplitude of the first longitudinal acoustic mode, near 93 Hz, when the secondary injection was pulsed at the same modal frequency. This was due to the uncontrolled phasing of the secondary injection system. A Pulse Width Modulated (PWM) signal was added to the open-loop control scheme to correct for improper phasing of the secondary injection flow relative to the primary flow. This addition allowed the motor speed to be intermittently increased to a higher RPM before returning to the desired open-loop control state. This proved to be effective in reducing the pressure disturbance by approximately 46%. A closed-loop control scheme was then test for its effectiveness in controlling the phase of the secondary injection. Feedback of the system's state was determined by placing a dynamic pressure transducer near the chamber exit. Closed-loop active control, using the designed secondary injection system, was proven as an effective means of reducing the problematic instabilities. A 50% reduction in the FFT RMS amplitude was realized by utilizing a Proportional-Derivative controller to modify the phase of the secondary injection.

京都大学 / 新制・課程博士 / 博士(エネルギー科学) / 甲第23535号 / エネ博第426号 / 新制||エネ||81(附属図書館) / 京都大学大学院エネルギー科学研究科エネルギー社会・環境科学専攻 / (主査)教授 河本 晴雄, 教授 石原 慶一, 教授 川那辺 洋 / 学位規則第4条第1項該当 / Doctor of Energy Science / Kyoto University / DFAM

Most combustion machines feature internal flows with very high energy densities. If a small fraction of the total energy contained in the flow is diverted into oscillations, large mechanical or thermal loads on the structure can be the result, which are potentially devastating if not predicted correctly. This is particularly the case for lightweight high performing devices like rockets. The problem is commonly known as "Combustion Instability". Several mechanisms have been identified in the past that link the flow field to the acoustics inside a combustion chamber and thereby drive or dampen oscillations, one of them being vortex shedding. The interaction between the highly sheared flow behind an obstacle and longitudinal acoustic oscillations inside a solid rocket booster is investigated both analytically and experimentally.The analytical approach is developed based on modeling of the second order acoustic energy. The energy model is applied to the specific flow conditions just downstream of a single baffle protruding into the flow. The mean flow profile is assumed to be of the form of a hyperbolic tangent, the unsteady acoustic velocities are assumed to be sinusoidally oscillating. Solutions for the unsteady rotational velocities and the unsteady vorticity are derived. The resulting flow field is utilized in stability calculations for a simplified two-dimensional axial-symmetric geometry. This yields to linear growth rates of the (longitudinal) oscillation modes. The growth rates are functions of the chamber geometry, the mean flow properties and the properties of the shear layer created by the flow restriction.A cold flow experiment is designed, tested and performed in order to validate the analytical findings. Flow is injected radially into a tube with acoustic closed-closed end conditions. A single baffle is installed in the tube, the axial position of the baffle is varied as well as its inner diameter. Frequency spectra of pressure oscillations are recorded. The experimental data is then compared qualitatively to the analytical growth rates. Those longitudinal Normal Modes, which feature the highest theoretical growth rates, are expected to be most prominent in the experimental data. This behavior is clearly observable.

As advanced nozzles may offer alternative solutions to conventional nozzles for the future class of reusable launch vehicles, a critical aspect is to tailor these novel technologies to current recovery strategies, more specifically to vertical landing sustained by retro-propulsion. Researchers at Technische Universität Dresden have developed a dedicated test-bench for the vacuum wind tunnel facility, where Advanced Nozzle Concepts (ANCs), such as aerospike and dual-bell nozzles, are tested in cold-gas configuration while invested by subsonic counter-flows. The main objective of the test campaign is to evaluate the performance and altitude–compensation characteristics of such ANCs by simulating a vertical landing manoeuvre through the variation of ambient pressure experienced during the landing burn. A detailed description of design and development of the test-bench, together with preliminary results from the commissioning activities, are here offered to the reader. The force measurements, together with pressure and temperature data, contribute to evaluate thrust levels and coefficients, as well as the monitoring of the interaction between the nozzle cold-flow and the opposing free-stream. A background-oriented schlieren system allows to visualise the external flow-field. In conclusion, an outline of the upcoming test campaign and a description of the expected results is offered.

To optimize biodiesel manufacturing, many reported studies have built simulation models to quantify the relationship between operating conditions and process performance. For mass and energy balance simulations, it is essential to know the four fundamental thermophysical properties of the feed oil: liquid density (Ï L), vapor pressure (Pvap), liquid heat capacity (CpL), and heat of vaporization (Î Hvap). Additionally, to characterize the fuel qualities, it is critical to develop quantitative correlations to predict three biodiesel properties, namely, viscosity, cetane number, and flash point. Also, to ensure the operability of biodiesel in cold weather, one needs to quantitatively predict three low-temperature flow properties: cloud point (CP), pour point (PP), and cold filter plugging point (CFPP). This article presents the results from a comprehensive evaluation of the methods for predicting these four essential feed oil properties and six key biodiesel fuel properties. We compare the predictions to reported experimental data and recommend the appropriate prediction methods for each property based on accuracy, consistency, and generality. Of particular significance are (1) our presentation of simple and accurate methods for predicting the six key fuel properties based on the number of carbon atoms and the number of double bonds or the composition of total unsaturated fatty acid methyl esters (FAMEs) and (2) our posting of the Excel spreadsheets for implementing all of the evaluated accurate prediction methods on our group website (www.design.che.vt.edu) for the reader to download without charge. / Master of Science

This paper examines two examples of testing activities of sub-components of a 300kN methalox first-stage rocket engine developed by Pangea Aerospace, namely, theinjectors and the cryogenic pumps. One of the difficulties of these test campaignsis to evaluate the performances of these sub-components without using cryogenicpropellants and in conditions differing from flight conditions.Two different methods were used to replace the cryogenic propellants at extreme pressures and temperatures: the pumps were tested using water to replace both propellants, and the injectors were tested using water and nitrogen to account for the different propellant phases. The correlation, similarity methods, and bench sizing were detailed for both test campaigns, but only the injector test campaign was completed and its results were analyzed.The method to emulate cryogenic fluid behavior in a pump leads to the use of a bench controlling not only pressure and mass flow but also temperature to account for the cavitation effects. Furthermore, the bench must have the capability to pressurize the water under atmospheric pressure, leading to the use of a vacuum pump. The injector test campaign produces results that closely align with theoretical predictions. This enables the selection of the optimal single-element injector design through a quantitative assessment of the discharge coefficient and a qualitative evaluation of the spray angle and atomization. Although these studies are based on strong models, they must be compared to hotfire data and later flight data to be assessed fully, all the more so that the pump test campaign was not performed. / I denna rapport behandlas två exempel på provningsaktiviteter för delkomponenter av en methalox-driven 300 kN-klass raketmotor, utvecklad av Pangea Aerospace för användning på förstasteg. Delkomponenterna består av injektorerna samt dekryogena pumparna. En av svårigheterna med provkampanjerna är att utvärdera prestandan hos dessa delkomponenter utan att använda kryogena drivmedel och underförhållanden som skiljer sig från flygförhållandena. Två olika metoder användes för att imitera de kryogena drivmedlen vid extrema tryck och temperaturer. Först testades pumparna med vatten som en ersättning för de båda drivmedlen, och sedan testades injektorerna med både vatten och kväve för att ta hänsyn till de olika aggregations tillstånden. Korrelationen, likhetsmetoderna, samt provbänkstorleken utredes i detalj för bägge testkampanjer, men endast injektortestkampanjen slutfördes och dess resultat analyserades. Metoden för att efterlikna kryogena vätskors beteende i en pump leder till användning av en provbänk som inte bara reglerar tryck och massflöde utan även temperatur för att ta hänsyn till kavitations effekterna. Dessutom måste bänken ha kapacitet att trycksätta vattnet under atmosfärstryck, vilket leder till användning av en vakuumpump. Injektortestkampanjen ger resultat som ligger nära de teoretiska förutsägelserna. Detta gör det möjligt att välja den optimala injektordesignen genom en kvantitativ bedömning av utloppskoefficienten och en kvalitativ bedömning av vinkeln och finfördelningen av injektorstrålen. Även om dessa studier baseras på starka modeller måste de jämföras med data från brännprover och senare flygdata för att kunna bedömas fullt ut, särskilt som pumptestkampanjen inte genomfördes.

Les gazoles, carburant automobile préféré des français, sont « additivés » afin de permettre leur utilisation en hiver. Les n-paraffines présentes dans ces gazoles cristallisent en effet à basse température. Ces cristaux peuvent alors entraîner le colmatage des filtres protecteurs situés en amont du moteur. Des polymères à base d'éthylène, notamment les copolymères éthylène-acétate de vinyle (EVA), sont utilisés pour abaisser la température à laquelle les problématiques de filtration adviennent. Un nouveau procédé de copolymérisation radicalaire d'éthylène et d'acétate de vinyle, à plus basse pression et à plus basse température, que le procédé industriel actuel, a été développé au cours de cette thèse. Une grande variété d'EVA a ainsi été obtenue. Ils présentent des caractéristiques structurelles et une efficacité, pour le traitement des gazoles, similaires aux EVA commerciaux. Ce procédé a, par ailleurs, permis la synthèse d'autres co- et terpolymères de l'éthylène variant par la nature des comonomères polaires utilisés ou par l'architecture. Des modèles de copolymères EVA ont été également synthétisés par métathèse. La grande diversité d'additifs polymères à disposition combinée à des techniques d'analyse thermique et de diffusion des rayons X mises en oeuvre au plus proche de l'application (en particulier dans le gazole), ont permis de mieux appréhender leur mode d'action sur la cristallisation des n-paraffines. Les spécificités structurelles, des polymères, conditionnant leur efficacité pour le traitement de la tenue à froid des gazoles ont également pu être établies / The additivation of diesel fuels allows operating engines at low temperatures without filter blocking and thus fulfilling legal requirements. Ethylene based copolymers such as ethylene-vinyl acetate copolymers, made by free radical polymerization at high pressure (above 2000 bars) and high temperature (above 200 °C) are frequently used as middle distillate cold flow improvers (MDFI). A new free radical copolymerization process of ethylene and vinyl acetate in organic solvent media has been developed. This process gives access to polymers close to commercial MDFI additives under tremendous less drastic conditions (under 250 bars of ethylene and 70 °C). Thanks to this process, a wide diversity (variation of the nature of the polar unit, of polymer architecture…) of ethylene based polymers was obtained. Moreover, EVA model copolymers have been synthesized by metathesis. Thanks to these numerous and diverse ethylene based polymers combined with thermal analysis and X-ray scattering studies a better understanding of the operating mode of these additives in a diesel fuel has been achieved. The structural characteristics of the polymers enabling their effectiveness as diesel fuel cold flow improvers have also been established

Ce travail s’inscrit dans le cadre de la prévision des oscillations de pression interne des moteurs à propergol solide. Il consiste à étudier la transition laminaire-turbulent de l’écoulement interne,modélisé par celui dans un conduit cylindrique à paroi débitante, et son lien avec l’instabilité naturelle de cet écoulement, le Vortex Shedding Pariétal (VSP). La démarche s’est organisée en trois temps. Des mesures antérieures sur un montage gaz froid, reproduisant l’écoulement modèle,sont analysées afin de mettre en évidence la transition laminaire-turbulent. Cette transition est ensuite imposée dans des simulations URANS afin de permettre l’étude de son influence sur les modes VSP. Enfin, une approche LES est mise en place pour simuler le développement de la transition dans les conditions de l’expérience ; dans ce but, une stratégie de perturbation spatiale de l’écoulement est utilisée. Cette étude met en avant quatre résultats principaux. La transition laminaire-turbulent découle de l’amplification spatiale des modes VSP. La simulation de ce processus met en évidence une forte influence de la perturbation numérique ajoutée à l’écoulement. D’autre part, les simulations URANS montrent que la transition réduit l’amplification des modes VSP et les oscillations de pression interne résultantes. Le rôle de la transition dans l’absence d’oscillations de pression lorsque le domaine a un grand rapport d’aspect, jusqu’alors supposé dans la littérature,est ainsi confirmé. Une particularité importante de cette transition est qu’elle dépend de la position radiale, l’écoulement étant turbulent près de la paroi débitante et laminaire au cœur. / The present work is related to the prediction of oscillations in solid rocket motors inner flow. It consists in a study of the laminar-turbulent transition of the motor’s inner flow, which is represented by a cylindrical injection-driven flow, and the relation between this phenomenon and the natural instability named Parietal Vortex Shedding (PVS). Three aspects have been analyzed.First of all, previous cold-gas experiments – reproducing the injection driven flow – are analyzed in order to highlight the transition laminar-turbulent transition. This transition is then imposedin URANS simulations to enable a study of its influence on the PVS modes. Finally, Large Eddy Simulations are performed to simulate the laminar-turbulent process. A strategy based on spatial steady disturbances is used to ease this process. The mains conclusions of this work are the following ones. The laminar-turbulent transition is a consequence of the spatial amplification of PVS modes. Simulations of this process highlight a strong influence of the injected numerical disturbances. The URANS simulations show that this transition reduces the amplification of PVSmodes, and the resulting pressure oscillations levels. These results confirm the role of the transitionin the absence of pressure oscillations when the motor cavity is long. A distinctive feature ofthis transition is its dependence on the radial position, which leads to the coexistence of a laminar region in the channel core and a turbulent region near the injecting wall at a given axial position.