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1
Dupont, Benoît. "Conception du compresseur supersonique du Rim Rotor Rotary Ramjet Engine." Mémoire, Université de Sherbrooke, 2015. http://hdl.handle.net/11143/8823.
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La demande pour les ressources énergétiques est en hausse alors que leur disponibilité est en baisse. Dans ce contexte, l’industrie du transport et de l’énergie est à la recherche de petits moteurs efficaces et puissants et le Rim Rotor Rotary Ramjet Engine (R4E) pourrait correspondre à ces critères. Or, en ce moment, le potentiel de ce moteur est limité, car son compresseur supersonique entraîne des pertes d’efficacité lorsque le rotor tourne à son nombre de Mach tangentiel optimal qui est de 2.
Le présent mémoire compile toutes les notions requises pour comprendre le fonctionnement d’un compresseur supersonique lors de son démarrage et de concevoir le compresseur le plus approprié pour le R4E, tant en démarrage qu’en régime permanent. Pour se faire, des concepts de cascades inspirés des compresseurs et des méthodes de démarrage des moteurs ramjet actuels ont été générés et validés à l’aide de modèles analytiques. Les concepts sont par la suite essayés expérimentalement sous la forme de cascades à l’aide d’une soufflerie supersonique.
Bien que le modèle analytique montre que les cascades munies de canaux de purge soient plus performantes et plus robustes en conditions off-design, ces dernières n’ont jamais démarré lors des expérimentations même si les canaux ont été agrandis et multipliés. Ainsi, parmi tous les concepts essayés, celui qui démarre par survitesse et qui comporte des canaux de succion de couche limite à son col a donné les meilleurs résultats. Il est très stable et permet d’obtenir un ratio de pression statique de 4.25 et un recouvrement de pression totale de 89 %, pour une efficacité isentropique de 92 % à un nombre de Mach tangentiel de 2. Par contre, il est à noter qu’il n’a pas été possible de mesurer la pression totale. Elle a plutôt été estimée à partir des images de strioscopie tirées lors des essais.
Comme on ne dispose pas d’une structure permettant d’essayer le compresseur rotatif à Mach 2, il a fallu approximer l’influence de l’accélération centrifuge sur l’écoulement de la cascade et trouver un moyen d’intégrer le nouvel aubage à la roue. Un modèle permettant d’estimer les paramètres d’une couche limite se développant sur une plaque plane en rotation a permis de déduire que l’accélération transverse n’aurait qu’un effet légèrement favorable, puisqu’il permet d’amincir l’épaisseur de déplacement, réduisant ainsi les risques d’interaction en la couche limite et les chocs. Finalement, les canaux de succion de couche limite du compresseur pourraient permettre d’alimenter un système de refroidissement qui limiterait la température à la jante à 820 K.
Le R4E pourrait devenir l’avenir des systèmes de régénération électrique pour les véhicules hybrides. Il serait aussi intéressant pour une utilisation dans les petites centrales thermiques des régions éloignées. Ce grand potentiel d’utilisation provient de la grande densité de puissance du moteur, de sa simplicité et de son très faible coût de fabrication et de maintenance.
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Bagheri, Amirhossein. "Preliminary Analysis of an Innovative Rotary Displacer Stirling Engine." Thesis, University of North Texas, 2015. https://digital.library.unt.edu/ark:/67531/metadc822801/.
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Stirling engines are an external combustion heat engine that converts thermal energy into mechanical work that a closed cycle is run by cyclic compression and expansion of a work fluid (commonly air or Helium) in which, the working fluid interacts with a heat source and a heat sink and produces network. The engine is based on the Stirling cycle which is a subset of the Carnot cycle. The Stirling cycle has recently been receiving renewed interest due to some of its key inherent advantages. In particular, the ability to operate with any form of heat source (including external combustion, flue gases, alternative (biomass, solar, geothermal) energy) provides Stirling engines a great flexibility and potential benefits since it is convinced as engines running with external heat sources. However, several aspects of traditional Stirling engine configurations (namely, the Alpha, Beta, and Gamma), specifically complexity of design, high cost, and relatively low power to size and power to volume ratios, limited their widespread applications to date. This study focuses on an innovative Stirling engine configuration that features a rotary displacer (as opposed to common reciprocating displacers), and aims to utilize analytical and numerical analysis to gain insights on its operation parameters. The results are expected to provide useful design guidelines towards optimization. The present study starts with an overview of the Stirling cycle and Stirling engines including both traditional and innovative rotary displacer configurations, and their major advantages and disadvantages. The first approach considers an ideal analytical model and implements the well-known Schmidt analysis assumptions for the rotary displacer Stirling engine to define the effects of major design and operation parameters on the performance. The analytical model resulted in identifying major variables that could affect the engine performance (such as the dead volume spaces, temperature ratios and the leading phase angle). It was shown that the dead volume could have a drastic effect over the engine performance and the optimum phase angle of the engine is 90o. The second approach considers a non-ideal analytical model and aims to identify and account the main sources of energy losses in the cycle to better represent the engine performance. The study showed that the ideal efficiency and the non-ideal efficiency could have 15% difference that could have as an enormous effect on the engine performance.
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DRUMOND, CARLO CESAR. "NUMERICAL SIMULATION OF A ROTARY STIRLING ENGINE." PONTIFÍCIA UNIVERSIDADE CATÓLICA DO RIO DE JANEIRO, 2017. http://www.maxwell.vrac.puc-rio.br/Busca_etds.php?strSecao=resultado&nrSeq=30089@1.
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PONTIFÍCIA UNIVERSIDADE CATÓLICA DO RIO DE JANEIROCOORDENAÇÃO DE APERFEIÇOAMENTO DO PESSOAL DE ENSINO SUPERIOR
PROGRAMA DE EXCELENCIA ACADEMICA
O presente trabalho estuda um motor de deslocamento positivo Stirling rotativo. Dois modelos de simulação para este motor Stirling rotativo são desenvolvidos. O primeiro modelo utiliza o método isotérmico, mediante o qual a câmara de expansão/compressão do motor está à mesma temperatura do reservatório térmico com que troca calor. O segundo modelo utiliza o método de volumes de controle, no qual o motor é dividido em cinco volumes de controle: as câmaras de expansão e compressão, o aquecedor, o resfriador e o compartimento rotativo. Para cada volume de controle aplicam-se as equações de conservação de massa e energia e de equações de estado do gás. O sistema de equações diferenciais ordinárias resultantes do segundo modelo, é integrado, permitindo obter-se a variação no ângulo do eixo para todas as variáveis termodinâmicas do motor (pressão, temperatura, etc.). Dadas as condições de operação e a geometria do motor rotativo em estudo, os modelos preveem resultados globais e transientes ângulo a ângulo. Os resultados dos modelos são confrontados com resultados teóricos disponíveis na literatura.
The present work studies a positive displacement rotary Stirling engine. Two simulation models for this rotary Stirling engine are developed. The first model applies the isothermal method, in which the gas at the engine expansion / compression chamber has the same temperatures of the thermal reservoir. The second model uses the control volume method, in which the engine is divided into five control volumes: the expansion and compression chambers, the heater, the chiller and the rotary chamber. For each control volume the equations of conservation of mass and energy and the equation of state, are applied. The system of ordinary differential equations resulting from the second model is integrated allowing to obtain the variation in the axis angle for all thermodynamic variables of the motor (pressure, temperature, etc.). Given the operating conditions and geometry of the rotating motor under study, the models provide global and transient results from angle to angle. Results from two models are confronted with theoretical results available in the literature.
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Picard, Mathieu. "Dynamique des gaz et combustion du Rim-Rotor Rotary Ramjet Engine (R4E)." Mémoire, Université de Sherbrooke, 2011. http://savoirs.usherbrooke.ca/handle/11143/1607.
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Le Rim-Rotor Rotary Ramjet Engine (R4E) a le potentiel de remplacer les turbines à gaz de 1 MW et moins en offrant : (1) une densité de puissance de 7.6 kW/kg, soit le double des turbines à gaz actuelles, (2) une meilleure fiabilité et un moindre coût par sa pièce mobile unique et (3) une efficacité de plus de 20 %, soit similaire aux turbines à gaz de cette puissance.Le R4E convertit la grande vitesse tangentielle du mélange air-carburant, idéalement 1000 m/s, en une grande pression dans la chambre de combustion. La combustion des réactifs augmente le volume du gaz ce qui force les produits à sortir à une grande vitesse tangentielle. La poussée générée est récupérée en travail mécanique à l'arbre directement ou est convertie en électricité. Ce travail présente la conception de la géométrie des propulseurs à l'aide d'un modèle 1D généralisé basé sur l'analyse préliminaire, ainsi que la validation expérimentale d'un prototype faisant la preuve de concept du R4E à travers 5 étapes principales s'étendant sur 2 versions du prototype : (1) la friction aérodynamique, (2) l'écoulement dans le moteur, (3) l'allumage, (4) la combustion et (5) la démonstration de la puissance nette des ailettes. La friction aérodynamique de la paroi externe du Rim-Rotor dépasse de 35 % les modèles actuels ce qui en fait le mécanisme de perte le plus important.Le débit massique dans le moteur est de 30 % inférieur à la valeur estimée par le modèle 1D pour la géométrie testée. La puissance de trainée des statoréacteurs sans combustion mesurée est en ligne avec la puissance prédite pour un débit massique corrigé expérimentalement. En ce qui concerne la combustion dans le moteur, le champ centrifuge extrême domine le mécanisme de propagation de la flamme. Un modèle simple de flottaison est utilisé pour prédire la longueur du front de flamme, représentant les produits chauds qui ont tendance à"flotter" sur les réactifs froids. Un modèle numérique est élaboré pour valider la propagation de la flamme jusqu'à une accélération centrifuge de 1.1 million de g et montre une bonne corrélation avec le modèle simple. Une efficacité de combustion de 85% est démontrée avec un second prototype pour une accélération centrifuge jusqu'à 284 000 g, soit 25 fois supérieures à la plus grande valeur testée dans la littérature. Une fois la combustion stabilisée, ce prototype a été en mesure de produire une légère poussée, une première pour les moteurs à statoréacteur rotatif.
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Rancourt, David. "Analyse structurelle et validation expérimentale d'un Rim-Rotor Rotary Ramjet Engine (R4E)." Mémoire, Université de Sherbrooke, 2011. http://savoirs.usherbrooke.ca/handle/11143/1612.
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Le Rim-Rotor Rotary Ramjet Engine (R4E) est un moteur très haute densité de puissance utilisant des statoréacteurs en rotation pour produire un couple à grande vitesse angulaire.Le design structurel d'une première génération de R4E est présenté dans ce mémoire ainsi qu'une validation expérimentale avec combustion haute température. Ces travaux s'imbriquent dans un programme de recherche où l'objectif ultime est de démontrer expérimentalement qu'il est possible de produire de la puissance positive de ce type de moteur. La structure principale du moteur est basée sur l'utilisation d'un Rim-Rotor, un anneau de Carbone-PEEK unidirectionnel, qui reprend partiellement le chargement des propulseurs en compression. Un moyeu en aluminium en une pièce inclut les propulseurs et supporte le système d'allumage inductif intégré à la structure. Ce dernier a été caractérisé indépendamment afin de connaître l'effet des paramètres tels la distance entre les électrodes sur la puissance et l'énergie des étincelles.Le concept final proposé pèse 76 g, ne contient que 5 pièces dans un assemblage unique et peut résister à une vitesse tangentielle de 330 m/s (120 krpm) au niveau des propulseurs lors d'une combustion d'hydrogène de 1 sec. Un autre concept présenté est conçu pour résister 560 m/s (200 krpm) pour des durées de combustion très courtes, sans échauffement significatif des composants. Un modèle structurel analytique est proposé et validé par un modèle numérique ainsi que des essais expérimentaux sans combustion réalisés jusqu'à 188 krpm sans rupture.Le prototype conçu pour la combustion est validé par rapport à ses paramètres de conception et une rupture des pales de turbine survient tel que prédit par le modèle couplé thermique-structurel numérique. Les recherches ont démontré que le concept d'un R4E est viable et qu'il a le potentiel d'atteindre une vitesse tangentielle de près de 1000 m/s en utilisant des matériaux disponibles aujourd'hui. Les dissimilitudes d'expansion thermique entre les composantes, la différence de rigidité entre les pièces de l'assemblage ainsi que le transfert de chaleur vers le Rim-Rotor ont été identifiés comme des considérations importantes pour les futurs concepts de R4E.
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Hudson, Barry, and not given. "The Production of Power by Pure Rotary Means." RMIT University. Architecture and Design, 2008. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20090213.150107.
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The chapters subsequent to the design discussion describe the evolution of the project. During the progression of the project, four case studies were undertaken. Each of these case studies involved the design of an engine, using the principles expounded in the early chapters. The parts of three of these were manufactured. The project has culminated in case study four which consisted of the conception, design and component manufacture of a new type of engine: the Hudson 5 Cycle Rotary Engine. It does not reciprocate, nor is it orbital (Sarich) and is not peritrocoidal (Mazda). It operates with pure rotary motion. It also promises to have a favourable environmental aspect due to its excellent fuel efficiency and because of its exceptional power to weight and power to size ratios plus a low component count. The small size and low number of parts make it very economical to produce, both in materials and energy.
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Stanten, Raymond Anthony. "Heat transfer and performance calculations in a rotary engine." Thesis, Massachusetts Institute of Technology, 1987. http://hdl.handle.net/1721.1/101304.
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Karaca, Mehmet. "Overal Performance Prediction Of Turbo Rotary Compound (turc) Engine Using Simulation Results Of Engine Components." Master's thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/2/12606491/index.pdf.
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The thesis proposes an overall performance estimation procedure for a new turbo-rotary compound engine (TURC) and an associated novel thermodynamic cycle. In this engine, two or multiple spools are lined up in series within the engine. In the front spool, positive displacement rotary vane type turbines drive axial compressor the performance of which were estimated using stage stacking calculations. In the back spool, axial turbine stages drive positive displacement rotary vane type compressors, the performance of axial turbine was predicted by series matching of turbine stages. Two air streams feed separately the customary turbo components and the rotary vane components, respectively. Accordingly, the primary high mass flow through the axial compressors and turbines undergoes Bryton cycle, where as the secondary, low mass flow through the positive displacement rotary components is mainly undergoes Akmandor cycle, which is a novel thermodynamic cycle. The energy consumed internally by the engine is minimized because less input shaft power is needed for the rotary vane compressors and higher inlet temperatures and less cooling can be tolerated by the intermittent combustion rotary vane turbines. The result is a radical improvement in both efficiency and net power output. But this result can be estimated, since the novel engine is the combination of a high efficiency internal combustion engine and high performance gas turbine engine. Aerothermodynamics and spool matching calculations comparing a T56-A14 core with a TURC of similar size and compression ratio show that the new engine provides superior performance characteristics by increasing the net output work by 100% and decreasing the specific fuel consumption by 20%.
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SILVA, FILIPE TEIXEIRA DE FREITAS E. "DEVELOPMENT AND EXPERIMENTAL EVALUATION OF A ROTARY INTERNAL COMBUSTION ENGINE." PONTIFÍCIA UNIVERSIDADE CATÓLICA DO RIO DE JANEIRO, 2018. http://www.maxwell.vrac.puc-rio.br/Busca_etds.php?strSecao=resultado&nrSeq=34206@1.
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PONTIFÍCIA UNIVERSIDADE CATÓLICA DO RIO DE JANEIROCOORDENAÇÃO DE APERFEIÇOAMENTO DO PESSOAL DE ENSINO SUPERIOR
PROGRAMA DE EXCELENCIA ACADEMICA
No presente trabalho foi realizada a construção, montagem, revisão de projeto e avaliação experimental preliminar de um novo motor a combustão interna rotativo por ignição por centelha, que pode ser classificado como cat-and-mouse engine ou Twin-Rotor Piston Engine. Nesse motor, dois pares de deslocadores são montados sobre dois rotores, que giram em velocidade variável em dentro de uma câmara cilindrica, de forma a conferir uma variação da posição angular relativa entre deslocadores e, assim, formar quatro câmaras de volumes variáveis com o tempo, a fim de se realizar processos termodinâmicos equivalentes aos de um motor alternativo de quatro tempos. Esse motor destaca-se por possuir um sistema inovador que permite a mudança do movimento dos rotores e deslocadores, de forma a aumentar o volume deslocado e a taxa de compressão das câmaras onde ocorrem os processos termodinâmicos. Tal dispositivo permite alterar e otimizar a taxa de compressão para diferentes combustíveis. Os componentes do motor foram usinados de acordo com o projeto e o protótipo foi montado, revisado e ajustado, de forma a garantir a operacionalidade do equipamento. Posteriormente, o motor foi montado em uma bancada para se efetuar testes preliminares de acionamento externo, afim de se medir vazão volumétrica, potência fornecida e pressão de compressão no ponto morto superior em função da velocidade angular. A revisão bibliográfica do trabalho contém definições úteis na classificação de motores rotativos, além de discutir suas especificidades características.
The present work describes the construction, assembly, project revision and preliminary experimental evaluation of an innovative rotary spark ignition internal combustion engine. First, a literature survey was carried out. Some useful definitions were found for rotary engines classification as well as some of their specific characteristics were discussed. The engine can be classified as cat-andmouse engine or Twin-Rotor Piston Engine. It is characterized by two pairs of displacers, assembled over two rotors, which rotate at a variable rotational speed within a cylindrical cavity. The driving mechanism is such that the relative distance between each pair of displacers varies continuously, thus providing the positive displacement effect. Therefore, the engine has four chambers, each one with its own time varying volume, so that thermodynamic processes, equivalent to those of a four-stroke reciprocating internal combustion engine, can take place. This engine presents a unique and innovative mechanism by which the compression ratio can be varied during operation, thus optimizing engine efficiency a for a given fuel. Engine components, designed in an effort previous to the present one, were fabricated according to the original project. A prototype was assembled, with all components following a routine of project revision, including measurements, uncertainties and adjustments. The engine was then placed on a test bench where preliminary non-firing external driving tests were carried out. They included: volumetric flow rate, driving (frictional) power and cylinder maximum pressure with displacer at the top dead center, all these parameters in terms of the primary shaft angular velocity.
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Tsakiroglou, G. B. "Performance modelling of a one-stroke rotary internal combustion engine." Thesis, University of Surrey, 1988. http://epubs.surrey.ac.uk/848135/.
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The subject of this Thesis is the performance modelling and evaluation of the Rotary Internal Combustion One-Stroke Engine specified in Patent Application number PCT/GB 84/0048. A mathematical model, capable of simulating the various changes that take place during the cycle of the engine, has been formed and applied to the engine for testing its performance. Before forming the model the dimensions of the engine were calculated by considering the stressing of the main movable parts of the engine such as the driveshaft, radial sealing wall and rotary piston, as well as the surface area to volume ratio. Also the timing and conditions under which the engine operates were speci--fied and used as input to the model. The model incorporates six subroutines namely, "DATUM" which stores all the input constants and variables, "GEOMETRY" which calculates various geometrical engine parameters, "COMBUST" and "EXPAND" which simulate the ignition delay/combustion and expansion respectively, and "PERFORMANCE" which calculates the various performance parameters of the engine. The above model was run with different sets of fuel-air ratios/speeds as input. The performance evaluated has been tabulated and a performance map of the engine drawn. Typical pressure-volume and heat flux diagrams were plotted. Further, the model was tested, with different sets of operating variables as input, to optimise the principal dimensions and timing of the engine. The model was validated by adaption to simulate a two-stroke internal combustion reciprocating piston engine and run with MAN-B&W L55GB engine data. The output was compared with the figures quoted by the engine manufacturers. The comparison was favourable. Once the model had been validated a direct comparison was made between the internal combustion rotary one-stroke engine and the MAN-B&W L55GB engine. Costs were analysed and proposals of possible methods of optimising the design of the above engine formulated.
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Resor, Michael Irvin. "COMPUTATIONAL INVESTIGATION OF ROTARY ENGINE HOMOGENEOUS CHARGE COMPRESSION IGNITION FEASIBILITY." Wright State University / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=wright1419010366.
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Ercan, Taylan. "Thermodynamic And Structural Design And Analysis Of A Novel Turbo Rotary Engine." Master's thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/12606482/index.pdf.
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A novel turbo rotary engine, operating according to a novel thermodynamic
cycle, having an efficient compression phase, a limited temperature combustion
phase followed by a long power extraction phase is designed. Thermodynamic and
structural design and analysis of this novel engine is carried out and two prototypes
are manufactured according to these analysis. High performance figures such as
torque, power and low specific fuel consumption are calculated. Also the component
tests of the manufactured prototypes are completed and their results are
demonstrated.
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Benthara, Wadumesthrige Asela A. "Computational Investigation of Optimal Heavy Fuel Direct Injection Spark Ignition in Rotary Engine." Wright State University / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=wright1313594631.
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Novotný, Petr. "Rotační motor pro motocykly." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-318540.
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Diploma thesis is focused on conceptual design of Wankel rotary engine with performance between 30-60 kW. Performance of designed engine is determined to 35 kW and volume of one chamber amounts to 245,58 cm^3. In this thesis are step by step calculated geometrical properties of each design group which are afterwards put into 3D data. There is also solved cooling system of designed engine and design of geometrical and characteristic properties of parts of cooling system. Last but, not least there is solved placement of designed engine into frame of motorcycle. As suitable motorcycle has been chosen Honda CBR125R because it has very advantageous layout of frame.
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Tessaro, Ioannes Paulus Bohn. "Caracterização da geometria e do funcionamento do conceito do motor rotativo de palhetas." reponame:Biblioteca Digital de Teses e Dissertações da UFRGS, 2012. http://hdl.handle.net/10183/142841.
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O conceito de um motor rotativo de palhetas é apresentado e o modelo que opera similar aos motores recíprocos dois tempos é analisado. Este motor é formado por estator cilíndrico, rotor descentralizado, palhetas radiais e tampas laterais, similar aos compressores de palhetas radiais. Parâmetros geométricos estão definidos para que o motor possua características similares a dois motores recíprocos comerciais igualmente modelados. Suas geometrias estão detalhadas, assim como a modelagem termodinâmica e suas hipóteses, as quais devido ao caráter comparativo do trabalho não têm grande influência no alcance dos objetivos. Em relação aos motores recíprocos, o novo conceito prospecta algumas vantagens: maior compacidade; menor nível de vibrações; maior facilidade de alteração da razão de compressão; possibilidade de produção e montagem em módulos; e devido a todas estas, as maiores possibilidades para o projeto, fabricação, montagem e operação dos motores. Para melhor entendimento de algumas tendências relativas a estas vantagens, a sensibilidade dos parâmetros geométricos é estudada, com variações nos diâmetros do estator e do rotor, na espessura do rotor e das palhetas, na excentricidade entre rotor e estator, e no número de palhetas do conceito. Este estudo demonstra características únicas do motor rotativo de palhetas, dentre elas, a variação da espessura do rotor se destaca por proporcionar a alteração do tamanho do motor sem modificar os demais aspectos. A excentricidade entre o rotor e estator demonstra grande potencial na capacidade de alterar a razão de compressão do equipamento, inclusive podendo ser modificada após a construção do motor ou até mesmo durante sua operação. Também se destaca o número de palhetas, o qual tem influência direta sobre a curva de torque do ciclo e a efetividade do posicionamento das janelas de admissão e exaustão. Com isto, é concluída a caracterização da geometria e do funcionamento do motor rotativo de palhetas, obtendo uma boa base para as próximas etapas de seu desenvolvimento.The concept of a rotary vane engine is presented and the model that operates similar to twostroke reciprocating engines is analyzed. This engine is formed by a cylindrical stator, decentralized rotor, radial vanes and side housing plates, similar to the radial vane compressors. Geometrical parameters are defined so that the motor has similar characteristics to two commercial reciprocating engines also modeled. Their geometries are detailed, as well as the thermodynamic model and its assumptions, which due to the comparative nature of the work do not have significant influence in achieving the objectives. With respect to reciprocating engines, the new concept is prospecting some advantages: higher compactness; lowest level of vibration; ease of adjustment of compression ratio; possibility of manufacture and assembly in modules; and due to all these, the numerous possibilities to the design, manufacture, assembly and operation of the engines. For a better understanding of some these advantages trends, the sensitivity of geometric parameters are studied, with variations in the diameters of the stator and rotor, in the thickness of the rotor and the vanes, in the eccentricity between rotor and stator, and in the number of vanes of the concept. This study demonstrates unique rotary vane engine characteristics, among them, the range of rotor thickness stands out for providing a change in engine size without changing other aspects. The eccentricity between the rotor and stator shows great potential for the ability to change the compression ratio of the equipment and can be modified even after the construction or even during operation of the engine. It also highlights the number of vanes, which has a direct influence on the torque curve of the cycle and the effectiveness of the positioning of inlet and exhaust ports. Therewith, the characterization of rotary vane engine geometry and operational design is complete, obtaining a good basis for its next development stages.
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Zhao, Wenyu. "A Probabilistic Approach for Prognostics of Complex Rotary Machinery Systems." University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1423581651.
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Behrens, Justin William. "Modification and Performance Evaluation of a Mono-valve Engine." OpenSIUC, 2011. https://opensiuc.lib.siu.edu/theses/638.
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AN ABSTRACT OF THE THESIS OF Justin W. Behrens, for the Master of Science degree in Mechanical Engineering, presented on June 24, 2011 at Southern Illinois University Carbondale. TITLE: MODIFICATION AND PERFORMANCE EVALUATION OF A MONO-VALVE ENGINE MAJOR PROFESSOR: Dr. Suri Rajan A four-stroke engine utilizing one tappet valve for both the intake and exhaust gas exchange processes has been built and evaluated. The engine operates under its own power, but has a reduced power capacity than the conventional 2-valve engine. The reduction in power is traced to higher than expected amounts of exhaust gases flowing back into the intake system. Design changes to the cylinder head will fix the back flow problems, but the future capacity of mono-valve engine technology cannot be estimated. The back flow of exhaust gases increases the exhaust gas recirculation (EGR) rate and deteriorates combustion. Intake pressure data shows the mono-valve engine requires an advanced intake valve closing (IVC) time to prevent back flow of charge air. A single actuation camshaft with advanced IVC was tested in the mono-valve engine, and was found to improve exhaust scavenging at TDC and nearly eliminated all charge air back flow at IVC. The optimum IVC timing is shown to be approximately 30 crank angle degrees after BDC. The mono-valve cylinder head utilizes a rotary valve positioned above the tappet valve. The open spaces inside the rotary valve and between the rotary valve and tappet valve represent a common volume that needs to be reduced in order to reduce the base EGR rate. Multiple rotary valve configurations were tested, and the size of the common volume was found to have no effect on back flow but a direct effect on the EGR rate and engine performance. The position of the rotary valve with respect to crank angle has a direct effect on the scavenging process. Optimum scavenging occurs when the intake port is opened just after TDC.
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Shrestha, Amit. "Development and Performance Evaluation of a Mono-Valve Engine." Available to subscribers only, 2009. http://proquest.umi.com/pqdweb?did=1879983291&sid=1&Fmt=2&clientId=1509&RQT=309&VName=PQD.
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Blažo, Marek. "Hnací ústrojí závodního Wankelova rotačního motoru." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-229075.
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The main aim of master’s thesis was to handle the computing proposal and the construction design of the powertrain of racing Wankel rotary engine with 300 kW power output and in the case of 9000 speed per minute. On the basic of these values was made the primary design of the rotary engine, design of the eccentric shaft and rotor housing. Mechanical stress and torsional vibrations of the eccentric shaft were analyzed by using the course of indicator diagram.
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Votaw, Zachary Steven. "Computational Study on Micro-Pilot Flame Ignition Strategy for a Direct Injection Stratified Charge Rotary Engine." Wright State University / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=wright1347895074.
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Slíva, Jakub. "Motocyklový rotační motor." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-378137.
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This master's thesis describes a concept of Wankel type rotary engine for use in motorcycle with estimated power between 70 – 80 kW. Basic geometry parameters of rotor and ports are calculated. Power output is then checked on equivalent piston combustion engine with central crank mechanism in 1D simulation model. Rotor is designed for use with oil cooling system. Rotor is checked for safe design by static FEM analysis by applying maximum pressure found out of 1D simulation model.
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Aran, Gokhan. "Aerothermodynamic Analysis And Design Of A Rolling Piston Engine." Master's thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608449/index.pdf.
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A rolling piston engine, operating according to a novel thermodynamic cycle is designed. Thermodynamic and structural analysis of this novel engine is carried
out and thermodynamic and structural variables of the engine were calculated. The losses in the engine, friction and leakage were calculated and their effects on the engine were demonstrated.
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Nyawo, Talent. "Design of a rotary valve for pressurised steam." Thesis, KTH, Maskinkonstruktion (Inst.), 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-192859.
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Denna rapport är gjord på ett examensarbete som var utfört på uppdrag av det svenska företaget Ranotor AB. Syftet var att utveckla en konceptuell lösning för en rotationsventil som skall fungera i en miljö med hög temperatur och högt tryck. Ventilen skall arbeta under höga rotationshastigheter, vilket kräver korta öppettider.Tekniska hjälpmedel såsom SolidWorks, ANSYS och MATLAB användes för att modellera och analysera de konceptuella lösningarna. Slutlösningen valdes från ett flertal olika koncept, varpå detta vidareutvecklades och optimerades. Betydande material och gastätningslösningar identifierades och utvärderades för att hitta den bästa lösningen. Optimering av individuella komponenter och hela anordningen gjordes med avseende på spänning, termisk- och dynamisk analys. De givna specifikationerna uppfylldes och resultaten var tillfredsställande. Resultaten ger en teoretisk bas för vidareutveckling och applicering av en rotationsventil in en miljö med hög temperatur och högt tryck.This Master thesis is a project commissioned by the Swedish company Ranotor AB. The objective of this thesis is to develop a conceptual solution for a rotary valve mechanism that has to work efficiently in a high-temperature and high-pressure environment. The valve is to operate at high rotational speeds which calls for very short opening time.Modern engineering tools namely Solidworks, Ansys and Matlab, were employed for modelling and analysis of the conceptual solution.The best design solution was selected from three developed concepts, and the selected concept was further developed and optimized. Major material candidates and gas-tight sealing solution were identified and evaluated and the optimal material and seal design was chosen. Optimization of the individual components as well as the whole assembly was performed based on stress, thermal and dynamic analysis. The given design specifications and functions were fulfilled and the results were satisfactory. The obtained results provide a theoretical foundation for the development and application of a rotary valve in high-temperature and high-pressure environment.
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Amirian, Hossein. "Design of a novel rotary compact power pack for the series hybrid electric vehicle : design and simulation of a compact power pack consisting of a novel rotary engine and outer rotor induction machine for the series hybrid electric vehicle powertrain." Thesis, University of Bradford, 2010. http://hdl.handle.net/10454/4446.
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Hybrid electric vehicles significantly reduce exhaust emissions and increase fuel economy. Power packs are the most fundamental components in a series powertrain configuration of a hybrid vehicle, which produce the necessary power to run the vehicle. The aim of this project is to design a compact power pack for a series hybrid vehicle, using virtual prototyping. The hybrid electric vehicle characteristics and configurations are analysed, followed by an explanation of the principles of induction machines. A new type of rotary induction machine with an outer rotor construction is designed to be coupled with the novel rotary internal combustion engine with rotating crankcase in order to form the compact power unit for the hybrid vehicle. The starting and generation performance of the designed machine is analysed by an electric machine simulator, called JMAG. ADVISOR software is studied and utilised to simulate the overall vehicle performance, employing different categories of power packs in the powertrain. Results show that the proposed compact power pack has the best performance in terms of fuel economy, emissions and battery charging compared to the existing power unit options. Over the city cycle, fuel economy is increased by up to 47 % with emission reduced by up to 36 % and over the highway cycle, fuel economy is increased by up to 69 % with emission reduced by up to 42 %.
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Drbal, Milan. "Termodynamický model Wankelova motoru o výkonu 11 kW." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-355455.
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The master’s thesis deals with the Wankel rotary engines and their 1D simulations using a thermodynamic simulation software for the piston engines. The necessary steps for creation of the equivalent model of the four-stroke three-cylinder combustion engine are provided. The engine used for the validation model was Aixro XR 50. The data measured on this engine during testing were used to validate the created thermodynamic model. The discharge coefficient calculation of the intake and the exhaust ports is shown. The 11kW engine design is created using validated thermodynamic model.
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Moda, Sunil Udaya Simha. "Computational Modeling and Analysis of Heavy Fuel Feasibility in Direct Injection Spark Ignition Engine." Wright State University / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=wright1300120730.
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Böhm, Michael. "Návrh radiálních těsnicích lišt pro Wankelův motor." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2019. http://www.nusl.cz/ntk/nusl-400484.
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The master’s thesis deals with analysis of sealing elements of Wankel engines and their design. The necessary steps for creation of the model of dynamics of apex seal are provided, whereby the resulting force loads are then obtained. Furthermore, the design of the apex seal spring, the choice of the material and the production jigs for the production of the spring itself are presented. The finished components are tested in the engine testing laboratory and the results evaluated.
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Alcalde, Murilo Priori. "Comparison of the mechanical properties of engine-driven nickel- titanium instruments manufactured by different thermal treatments." Universidade de São Paulo, 2018. http://www.teses.usp.br/teses/disponiveis/25/25147/tde-24012019-101418/.
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The aim of this study was to evaluate the mechanical properties of engine-driven Nickel-Titanium instruments manufactured by different thermal treatments. In the first part of this study, 60 reciprocating instruments were used (n=20): Reciproc R25 (REC 25.08), Unicone L25 (UNC 25.06) e Prodesign R 25 (PDR 25.06). The cyclic flexural fatigue resistance was performed measuring the time to failure in an artificial stainless steel canal with a 60º angle and a 5 mm radius of curvature (n=10). The torsional test was performed according to ISO 3630-1, measuring the torque and angle of rotation at failure in the 3 mm from the tip portion (n=10). Additionally, the fractured surface of each instrument was examined by scanning electron microscopy (SEM) to assess the topographic features of the fractured surface. Data were analyzed using one was analysis of variance ANOVA and Tukey test, the level of significance was set at 5%. The results of the cyclic flexural fatigue showed that PDR 25.06 presented significantly higher values than the other groups (P<0.05). REC 25.08 showed higher fatigue resistance than UNC 25.06 (P<0.05). In relation to the torsional test, the PDR 25.06 presented the lowest torque load than REC 25.08 and UNC 25.06 (P<0.05). In addition, there was no significant difference between REC 25.08 and UNC 25.06 (P>0.05). The PDR 25.06 and UNC 25.06 showed higher angular rotation until fracture than REC 25.08 (P<0.05). No difference was found between PDR 25.06 and UNC 25.06. All the instruments showed typical topographic features of cyclic flexural and torsional fatigue. The second part of this study evaluated the cyclic flexural and torsional fatigue resistance of reciprocating instruments Reciproc Blue (RB 25.08), WaveOne Gold Primary (WOG 25.07) and Prodesign R 25 (PDR 25.06) (n=20). The cyclic flexural fatigue test was performed with the same previsoly described device, using a root curvature with 60º and a 5 mm radius (n=10) and the torsional test was performed according to ISO 3630-1 (n=10). The fractured surface of each instrument was examined by scanning electron microscopy (SEM). Data were analyzed using one was analysis of variance ANOVA and Tukey test, the level of significance was set at 5%. The results of the cyclic flexural fatigue test showed that PDR 25.06 presented significantly higher values than the other groups (P<0.05). RB 25.08 showed higher fatigue resistance than WOG 25.07 (P<0.05). The torsional test showed that PDR 25.06 had lowed torsional load (P<0.05). No difference was found between RB 25.08 and WOG 25.07 (P>0.05). In relation the angular rotation, the PDR 25.06 showed higher angular rotation values than RB 25.08 and WOG 25.07 (P<0.05). RB 25.08 presented higher angular values than WOG 25.07 (P<0.05). All the instruments showed typical topographic features of cyclic flexural and torsional fatigue. The third part of this study was to evaluate the torsional fatigue resistance of NiTi rotary glide path instruments. The torsional test was performed according to ISO 3630-1, measuring the torque and angle of rotation at failure in the 3 mm from the tip portion. A total of 56 glide path instruments were used (n=8): Logic 25.01 (LOG 25.01), Logic CM 25.01(LOG CM 25.01), Proglider 16.02 (PGD 16.02), Hyflex GPF 15.01, 15.02, 20.02 (HGPF) and Mtwo 10.04. The fractured surface of each instrument was examined by scanning electron microscopy (SEM). Data were analyzed using one was analysis of variance ANOVA and Tukey test, the level of significance was set at 5%. The results showed that LOG 25.01 had a significantly higher torsional load than the other groups (P<0.05). The PGD 16.02 had significantly difference in comparison with HGPF 15.01 and 15.02 (P<0.05). LOG CM 25.01 had higher torsional load than HGPF 15.01 and 15.02 (P<0.05). No difference was found among Mtwo 10.04, HGPG 15.01, 15.02 and 20.02. In relation the angular rotation, LOG CM 25.01 and HGPF 15.01 presented the highest values (P<0.05). PGD 16.02 had the lowest values (P<0.05) followed by Mtwo 10.04. LOG 25.01 had higher angle of rotation than PGD 16.02 and Mtwo 10.04 (P<0.05). All the instruments showed typical topographic features of torsional fatigue.O objetivo deste estudo foi avaliar o comportamento mecânico de instrumentos mecanizados de Níquel-Titânio (NiTi) fabricados com diferentes tratamentos térmicos. Na primeira parte do estudo foram utilizados 60 instrumentos reciprocantes para a realização dos teste de fadiga cíclica flexural e torcional (n=20): Reciproc R25 (REC 25.08), Unicone L25 (UNC 25.06) e Prodesign R 25 (PDR 25.06). O teste de fadiga cíclica flexural foi realizado com o objetivo de mensurar o tempo para a fratura dos instrumentos em um canal artificial de aço inoxidável com curvatura com 60º de angulação e 5 mm de raio (n=10). Para o teste de torção, os 3 mm inicias das pontas dos instrumentos foram fixadas em um aparelho de torção (n=10), de acordo com a norma ISO 3630-1. Este teste foi realizado com o objetivo de mensurar o torque máximo e o ângulo de rotação suportado pelos instrumentos até sua fratura. Adicionalmente, todos os fragmentos dos instrumentos fraturados foram examinados em microscopia eletrônica de varredura (MEV) para avaliar as características topográficas da superfície da área da fratura. A análise-estatística foi realizada utilizando o teste de análise de variância com um fator ANOVA e teste de Tukey, o nível de significância foi de 5%. Os resultados de fadiga cíclica flexural demonstraram que o PDR 25.06 apresentou maior tempo para a fratura do que os outros grupos (P<0.05). O instrumento REC 25.08 apresentou maior resistência a fadiga cíclica flexural do que o UNC 25.06 (P<0.05). O teste de torção demonstrou que o PDR 25.06 apresentou significantemente menor resistência torcional do que o REC 25.08 e UNC 25.06 (P<0.05). Além disso, não houve diferença entre REC 25.08 e UNC 25.06. Com relação ao ângulo de rotação, o PDR 25.06 e UNC 25.06 apresentaram diferença significante quando comparado ao REC 25.08. Não houve diferença entre PDR 25.06 e UNC 25.06 (P>0.05). Todos os instrumentos apresentaram característica topográficas típicas de fadiga cíclica flexural e torcional. Na segunda parte deste estudo avaliou-se a fadiga cíclica flexural e torcional dos instrumentos reciprocantes Reciproc Blue R25 (RB 25.08), WaveOne Gold Primary (WOG 25.07) e Prodesign R 25 (PDR 25.06) (n=20). O teste de fadiga cíclica flexural foi realizado com dispositivo descrito anteriormente, utilizando curvaturas de 60º e 5 mm de raio (n=10). O teste de torção foi realizado de acordo com a norma ISO 3630-1 (n=10). Todos os fragmentos dos instrumentos fraturados foram examinados em microscopia eletrônica de varredura (MEV) para avaliar as características topográficas da superfície da área da fratura. A análise-estatística foi realizada utilizando o teste de análise de variância com um fator (ANOVA) e teste de Tukey, o nível de significância foi de 5%. Os resultados de fadiga cíclica flexural demonstraram que o PDR 25.06 apresentou a maior resistência a fadiga cíclica flexural do que dos outros grupos (P<0.05). O RB 25.08 apresentou maior tempo para à fratura do que o WOG 25.07 (P<0.05). O teste de torção, o PDR 25.06 apresentou a menor resistência à torção do que os outros grupos (P<0.05). Não houve diferença significante entre RB 25.08 e WOG 25.07 (P>0.05). Em relação ao ângulo de rotação, o PDR 25.06 apresentou maiores valores quando comparados com RB 25.08 e WOG 25.07. O RB 25.08 apresentou diferença significante quando comparado com WOG 25.07. Todos os instrumentos apresentaram características topográficas típicas de fadiga cíclica flexural e torcional. Na terceira parte deste estudo avaliou-se a resistência torcional de instrumentos empregados para patência do canal radicular, de acordo com a norma ISO 3630-1. Foram utilizados 56 instrumentos rotatórios (n=8): Logic 25.01 (LOG 25.01), Logic CM 25.01 (LOG CM 25.01), Proglider 16.02 (PGD 16.02), Hyflex GPF 15.01, 15.02, 20.02 (HGPF) e Mtwo 10.04. Os fragmentos dos instrumentos fraturados foram examinados em microscopia eletrônica de varredura (MEV) para avaliar as características topográficas da superfície da área da fratura. A análise-estatística foi realizada utilizando o teste de análise de variância com um fator ANOVA e teste de Tukey, o nível de significância foi de 5%. Os resultados demonstraram que o LOG 25.01 apresentou significantemente maior resistência torcional do que os demais grupos (P<0.05). O grupo da PGD 16.02 apresentou diferença significante quando comparado com HGPF 15.01 e 15.02 (P<0.05). O LOG CM 25.01 apresentou maior resistência torcional do que o grupo do HGPF 15.01 e 15.02 (P<0.05). Não houve diferença significante entre os intrumentos Mtwo 10.04 e HGPF 15.01, 15.02 e 20.02. Com relação ao ângulo de rotação, o LOG CM 25.01 e HGPF 15.01 apresentaram os maiores valores (P<0.05). O PGD 16.02 apresentou o menor valor de todos os grupos (P<0.05) seguido pelo Mtwo 10.04. O LOG 25.01 apresentou maiores ângulos de rotação do que o PGD 16.02 e Mtwo 10.04 (P<0.05). Todos os instrumentos apresentaram característica topográficas típicas de fadiga torcional. As características da secção transversal, tipo de núcleo, taper e o tratamento térmico possuem forte influência sobre as propriedades mecânicas dos instrumentos de NiTi. No entanto, o tratamento térmico é um dos fatores primordiais para maior flexibilidade dos instrumentos. O instrumento PDR 25.06 apresentou maior resistência à fadiga cíclica flexural e maior ângulo de rotação no teste de torção do que todos os outros instrumentos reciprocantes avaliados. No entanto, menor resistência torcional. Os intrumentos LOG 25.01 apresentaram maior resistência torcional e o LOG CM 25.01 maiores ângulos de rotação.
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Andersson, Victor. "Flödesanalys av roterande ventil i ångmotor." Thesis, Karlstads universitet, Fakulteten för hälsa, natur- och teknikvetenskap (from 2013), 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kau:diva-68099.
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This report is a bachelor thesis at Karlstad University in collaboration with Invencon AB and Ranotor AB. The goal was to analyze a rotating valve leading water vapor through an inlet and five outlets. The quantifiable results that were addressed in this project are the mass flow through the outlets and the forces affecting the valve and its shaft (primarily radial forces). The tools used for this project are PTC Creo and ANSA for modelling and mesh as well as ANSYS-CFX and Matlab for computational help. The results show that the specified rotational speed of 4600 rpm doesn’t work for this model. The rotational speed was chosen because of an interest in this specific operating condition. A 3 mm radial gap between the rotating valve and the valve housing proved to cause a leakage in the form of pressure loss inside the valve. The boundary conditions that were laid out for this project are not valid for this operating condition. Since the difference in pressure is large (100 down to 1 bar) the flow is choked. A large difference in pressure also makes it important to adjust the total area of the outlets, since the pressure drop affects the density of the vapor. The forces on the rotating valve that were calculated (using ANSYS-CFX) create a foundation for choosing bearings for the valve. If the construction is modified, and/or the rotating valve will operate at a different rotational speed these forces will be subject to change.Denna rapport är ett examensarbete på Karlstads Universitet i samband med Invencon AB och Ranotor AB. Målet var att analysera en roterande ventil som leder trycksatt vattenånga via ett inlopp och ut genom fem olika utlopp. De kvantifierbara resultaten som söktes var massflödet ut ur utloppen och krafterna som påverkar ventilen och axeln (främst radiellt). Verktyg som har använts för att analysera ventilen är PTC Creo och ANSA för modellering och mesh, samt ANSYS-CFX och Matlab för beräkningshjälp. Resultaten tyder på att det valda varvtalet, 4600 rpm, inte fungerar så bra. Varvtalet valdes pågrund av att man var intresserad av driftsfallet. Ett 3 mm radiellt avstånd mellan ventil ochventilhus visade sig även ge läckage i form av tryckfall inuti ventilen. Randvillkoren som är specificerade är inte giltiga vid detta driftsfall. Eftersom tryckförhållandet är så högt (100 till 1 bar) så är flödet chokat. Stor tryckskillnad gör det viktigt att anpassa arean på utloppen, då tryckfall påverkar densiteten. Krafterna på den roterande ventilen som beräknades (i ANSYS-CFX) är ett underlag vid val av lager för ventilen. Om konstruktionen modifieras, och/eller ventilen kommer att användas vid ett annat varvtal så kommer dessa krafter att ändras.
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Krejčí, Tomáš. "Variabilní geometrie sacích a výfukových portů Wankelova motoru." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-229126.
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The purpose of this thesis is to design the key parameters of the high-powered Walkel engine and to design a chamber side on the base of computed parameters so that it enables variable change of the intake and exhaust port geometry. Consequently, to carry out a flow simulation in both ports in designed chamber side in order to find out its flow character and geometry change reaction.
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Dogantimur, Erkan, and Daniel Johnsson. "Analysis of Accuracy for Engine and Gearbox Sensors." Thesis, Uppsala universitet, Institutionen för teknikvetenskaper, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-388346.
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This thesis provides a standardized method to measure accuracy for engine and gearbox sensors. Accuracy is defined by ISO 5725, which states that trueness and precision need to be known to provide a metric for accuracy. However, obtaining and processing the data required for this is not straight forward. In this thesis, a method is presented that consists of two main parts: data acquisition and data analysis. The data acquisition part shows how to connect all of the equipment used and how to sample and store all the raw data from the sensors. The data analysis part shows how to process that raw data into statistical data, such as trueness, repeatability and reproducibility for the sensors. Once repeatability and reproducibility are known, the total precision can be determined. Accuracy can then be obtained by using information from trueness and precision. Besides, this thesis shows that measurement error can be separated into error caused by the sensors and error caused by the measurand. This is useful information, because it can be used to assess which type of error is the greatest, whether or not it can be compensated for, and if it is economically viable to compensate for such error. The results are then shown, where it is possible to gain information about the sensors’ performance from various graphs. Between Hall and inductive sensors, there were no superior winner, since they both have their strengths and weaknesses. The thesis ends by making recommendations on how to compensate for some of the errors, and how to improve upon the method to make it more automatic in the future.
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Rosa, Danielle Cristina. "Análise comparativa ex vivo da quantidade de material extruído apicalmente por diferentes técnicas mecanizadas de instrumentação dos canais radiculares." Universidade de São Paulo, 2009. http://www.teses.usp.br/teses/disponiveis/58/58133/tde-19032010-105032/.
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O tratamento endodôntico é constituído por uma sequência de fases que devem ser respeitadas e conduzidas com o mesmo grau de importância para o sucesso da terapia endodôntica. Atenção especial é dada a fase do o preparo biomecânico do canal radicular, que pode ocasionar extrusão de restos pulpares, tecido necrosado, rapas de dentina e substâncias químicas auxiliares através do forame apical, provocando uma reação inflamatória ou flare-up. Com o intuito de se obter um pós-operatório com êxito, realizou-se um estudo com o objetivo de avaliar, ex vivo, a quantidade de material extruído através do forame apical durante o preparo do canal radicular pelas seguintes técnicas: manual Step-Back, mecanizada rotatórias Crown Down e Free Tip Preparation. Trinta incisivos inferiores foram distribuídos aleatoriamente em 3 grupos (n=10), de acordo com as seguintes técnicas de instrumentação: G1- técnica manual Step Back (controle); G2- Crown Down; G3- Free Tip Preparation. Todos os grupos foram instrumentados a 0,5mm aquém do forame apical. O material extruído foi coletado em um Dispositivo Coletor de Material Extruído(DCME), confeccionado especificamente para essa finalidade e a extrusão apical foi calculada pela determinação da massa de material sólido extruído. Os valores obtidos foram analisados pelo teste de Kruskal- Wallis e o teste complementar de Dunn`s Multiple, com P=0.05, como nível de significância estatística. Os resultados mostraram que a técnica Step-Back promoveu maior quantidade de material extruído através do forame apical; e que não houve diferença estatística significante entre as técnicas Crown Down e Free Tip Preparation. Pode-se concluir também que houve extrusão de material sólido através do forame apical em todas as técnicas de instrumentação estudadas.Endodontic treatment is constituted of a sequence of stages that must be respected and performed with the same degree of importance in order to ensure the success of endodontic therapy. Special attention is paid to the stage of biomechanical preparation of the root canal, which may cause the extrusion of pulp remainders, necrotic tissue, dentin scrapings and auxiliary chemical substances through the apical foramen, causing an inflammatory reaction or flare-up. With the intention of achieving successful post-operative period, a study was conducted with the aim of making an ex vivo evaluation of the quantity of material extruded through the apical foramen during root canal preparation, by means of the following techniques: manual Step-Back, mechanized rotary Crown Down and Free Tip Preparation. Afterwards, the teeth were randomly assigned to three equal groups (n=15) according to post length, as follows: G1 manual Step-Back technique (control); G2 - Crown Down; G3 - Free Tip Preparation. All the groups were instrumented to 0.5 mm short of the apical foramen. The extruded was collected in an Extruded Material Collecting Device (EMCD), made specifically for this purpose, and apical extrusion was calculated by determining the mass of solid material extruded. The values obtained were analyzed by the Kruskal-Wallis test and complementary Dunns Multiple test, with P=0.05, as the level of statistical significance. The results showed that the Step-Back technique promoted the largest amount of material extruded through the apical foramen; and that there was no statistically significant difference between the Crown Down and Free Tip Preparations. It could also be concluded that there was extrusion of solid material through the apical foramen in all the studied instrumentation techniques used.
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Bagheri, Amirhossein. "Characterization, Analysis, and Optimization of Rotary Displacer Stirling Engines." Thesis, University of North Texas, 2019. https://digital.library.unt.edu/ark:/67531/metadc1609074/.
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This work focuses on an innovative Rotary Displacer SE (RDSE) configuration for Stirling engines (SEs). RDSE features rotary displacers instead of reciprocating displacers (found in conventional SE configurations), as well as combined compression and expansion spaces. Guided by the research question "can RDSE as a novel configuration achieve a higher efficiency compared to conventional SE configurations at comparable operating conditions?", the goal of this study is to characterize, analyze, and optimize RDSE which is pursued in three technical stages. It is observed the RDSE prototype has an optimum phase angle of > 90° and thermal efficiency of 15.5% corresponding to 75.2% of the ideal (Carnot) efficiency at the source and sink temperatures of 98.6° C and 22.1° C, respectively. Initial results indicate that 125° phase angle provides more power than that of the theoretically optimum 90° phase angle. The results also show comparable B_n and significantly higher W_n values (0.047 and 0.465, respectively) compared to earlier studies, and suggest the RDSE could potentially be a competitive alternative to other SE configurations. Furthermore, due to lack of a regenerator, the non-ideal effects calculated in the analytical approach have insignificant impact (less than 0.03 kPa in 100 kPa). The clearance volume in the shuttled volume has a dramatic negative effect and reduces the performance up to 40%. Ultimately, utilizing CFD, it is proved that the existing geometry is relatively optimized where the optimum phase angle is 121° and geometric ratio D\/L for the displacer is 0.49.
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Choy, Jose. "Wankel engine dynamic supercharging and surface rotor cooling." Thesis, University of Birmingham, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.497868.
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Romanov, Artyom. "Rocket Engine System Analysis : Vinci Engine Turbines Analysis, Volvo Aero Corp." Thesis, Linköping University, Linköping University, Linköping University, Applied Thermodynamics and Fluid Mechanics, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17766.
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Major part of the current work describes the development of the update methodology for onedimensional code (TML) currently used at Volvo Aero Corporation during turbine design process. The methodology is then applied and tried out in a general engine analysis (GESTPAN).
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Duran, Celio. "Modélisation du comportement dynamique non-linéaire et transitoire de turbomoteur avec multitouches rotor/stator." Thesis, Lyon, INSA, 2014. http://www.theses.fr/2014ISAL0144.
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Cette thèse traite de la dynamique non-linéaire multi-contact des ensembles rotor/stator et s’applique en particulier aux tur-bomoteurs d’hélicoptère conçus par Turboméca, groupe Safran. L’amélioration des performances des turbines à gaz pousse les constructeurs à réduire les jeux fonctionnels rotor-stator no-tamment, tout en garantissant robustesse et fiabilité. Cela nécessite de développer des modèles les plus précis possible afin de prévoir et maîtriser des situations à risques telles que les interactions rotor/stator entre les parties fixes et tournantes déclen-chées principalement, dans le cas des turbomoteurs d’hélicoptère, par la perte d’aubes. La partie 1 présente une synthèse bibliographique des principaux phénomènes physiques rencontrés suite à une touche ro-tor/stator en s’appuyant sur l’expérimentation et le calcul. Un bilan sur les différents modèles numériques de gestion du con-tact frottant est détaillé. La dualité entre méthodes temporelles et fréquentielles est aussi abordée comme la méthode de la ba-lance harmonique et les schémas d’intégration temporelle de la famille de Newmark. Il est aussi décrit deux outils d’analyse fréquentielle : le spectrogramme pour analyser l’évolution d’un spectre fréquentiel dans le temps, le full-spectrum pour pren-dre en compte les précessions du rotor. La partie 2 se focalise sur des systèmes dynamiques académiques : un oscillateur forcé à double butées, un rotor de Jeffcott et un rotor à 3 disques avec tous deux une interaction disque/carter. Compte tenu du caractère transitoire du comportement des turbomoteurs, il s’agit de tester des méthodes d’intégration temporelle pas à pas et aussi des lois de contact. Il en ressort que la méthode de Newmark à accélération moyenne, et les lois de contact type « pénalité amortie » combinées à une régularisation de la raideur et de l’amortissement par une fonction arc tangente sont pertinentes. La modélisation de rotor en flexion en ré-gime transitoire et avec plusieurs touches possibles est réalisée avec la méthode des éléments finis et l’intégration des mé-thodes et techniques précédentes. L’ensemble de la modélisation est mise en œuvre sous l’environnement Matlab et se traduit au final par un logiciel nommé ToRoS (Touche Rotor-Stator). Le turbomoteur de l’Ardiden 1H fait l’objet de la dernière partie. Le logiciel ToRoS développé est utilisé pour prévoir la dyna-mique transitoire de sa turbine libre soumise à de multiples touches, consécutifs à un départ d’aubes. Les lois de contacts ap-pliquées dépendent du type de contact : disque/carter, labyrinthe/stator, palier/butée. Durant la descente en vitesse, la ligne d’arbre adopte, en fonction du niveau de balourd, de la vitesse de rotation, des paramètres du contact et du frottement, un comportement avec un contact quasi-permanent en précession directeThis PhD thesis deals with the nonlinear transient dynamic response of rotor/stator assemblies in the case of multi-contacts, it is applied on Turbomeca’s helicopter turbo-engine. In order to improve gas turbine performances, constructors have to reduce rotor/stator clearances, while continuing to maintain component’s reliability, durability and safety. It implies the development of models to predict and control unsafe situations as, rotor/stator interactions between fixed and rotating parts, mainly triggered by a blade-loss in helicopters turbo-engine case. The first part of this document is concerned with a bibliographical summary of the main physical phenomena observed after a rotor/stator interaction, this is supported by experiments and numerical calculations. A review of the various sliding contact numerical models is presented. The duality between time and/or frequency simulation response methods as, harmonic balance method vs Newmark time integration scheme is discussed. Then two numerical tools for frequency domain analysis are described: the spectrogram to analyze frequency spectrum as a function of the time, the full-spectrum for analyzing the rotor whirl motions. The second part is focused on the time response simulation of some academic systems: an excited oscillator with two end-stops, a Jeffcott rotor and finally a 3 disks rotor both subjected to disk/casing interactions. Given the transient behavior exhibited by turbo-engine rotors following a rotor/stator contact, the purpose is to test several step-by-step time integration scheme combined with different contact laws. This analysis has shown that the Newmark scheme with constant acceleration used with damped contact penalty laws combined to stiffness and damping coefficients smoothed by arctangent functions are relevant. The rotor bending modeling during transient motion considering possible multi-contacts with the stator is realized using the finite element method and the previously reviewed contact modeling methods. The simulation is implemented under Matlab environment and is named ToRoS. (Rotor/Stator Touch). Finally, the developed modeling is applied to the Ardiden 1H turbo-engine. The ToRoS software is used to predict the transient dynamic response of the free power turbine subjected to multi-contacts, after a sudden blade-loss which is modeled by a sudden unbalance. Contact laws are applied and depend on contact type and location: disk/casing, seals, thrust bearing. Depending on the mass unbalance level, the speed of rotation, the contact and friction parameters, the rotor can be in a quasi-permanent contact state in forward whirl while the rotation speed is running-down
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Mok, Keng Wa. "Design and control of an electromechanical variable rotary valve system for four-stroke engines." Thesis, University of Macau, 2008. http://umaclib3.umac.mo/record=b1942819.
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Bolger, John Jude. "Three dimensional design of compressor blades." Thesis, University of Cambridge, 1999. https://www.repository.cam.ac.uk/handle/1810/251477.
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Quackenbush, John Charles. "Design, fabrication and test of a gas turbine engine and wave rotor test bed." Diss., Connect to online resource - MSU authorized users, 2008.
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Neilson, Richard David. "Dynamics of simple rotor systems having motion dependent discontinuities." Thesis, University of Dundee, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.362927.
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Picard, Mathieu. "Development of multiscale models for the performance of the gas and oil seals in rotary engines." Thesis, Massachusetts Institute of Technology, 2014. http://hdl.handle.net/1721.1/92169.
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Thesis: Ph. D., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2014.Cataloged from PDF version of thesis.
Includes bibliographical references (pages 341-344).
Rotary engines offer higher power density, fewer parts and lower vibrations than conventional reciprocating piston engines. However, rotary engines are more difficult to seal because of the rotor shape which leads to higher gas leakage and oil consumption resulting in lower efficiency and higher emissions. In order to address this problem, this thesis presents a set of multiscale models to assess rotary engine performances by estimating gas leakage, oil consumption, wear and friction. An oil seal multiscale model is developed to estimate internal oil consumption guided by oil transport visualization experiments carried using a laser-induced fluorescence technique. A finite element beam model is used to predict the clearance between the oil seals and the side housing for each crank angle in the cycle. From seal-housing clearance, oil transport through the oil seals is calculated using a control volume approach. The main mechanism leading to internal oil consumption is outward scraping of the oil seals due to a lack in conformability of the seals to the distorted side housing, especially next to the intake and exhaust ports. A set of multiscale models are developed for the performance of the apex and side seals. The models are formulated to couple gas flow to the dynamics and deformation of the seals while accurately describing the interfaces between the seals and their profile and groove. The models are used to predict apex and side seal behavior and understand the mechanisms leading to gas leakage. The main leakage mechanisms identified are leakage through (1) the corner seal clearance, (2) the spark plug holes, (3) the flanks of the seals at high speed, and (4) the side piece corner for the apex seals and at the ends of the side seals. The apex seal model shows good agreement with experiments, especially for the pressure in the apex seal groove. It is the first time such comprehensive models are developed for rotary engines and they will be valuable tools to help design more efficient and environment-friendly rotary engines.
by Mathieu Picard.
Ph. D.
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Pollock, Brad. "COMPUTATIONAL STUDY OF DIRECT FUEL INJECTION IN THE ROTAX 914 ENGINE." Wright State University / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=wright1292869654.
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Green, T. "Effect of external flow on the sealing performance of rotor-stator rim seals." Thesis, University of Sussex, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.358187.
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Suhr, Stephen Andrew. "Preliminary Turboshaft Engine Design Methodology for Rotorcraft Applications." Thesis, Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14128.
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In the development of modern rotorcraft vehicles, many unique challenges emerge due to the highly coupled nature of individual rotorcraft design disciplines therefore, the use of an integrated product and process development (IPPD) methodology is necessary to drive the design solution. Through the use of parallel design and analysis, this approach achieves the design synthesis of numerous product and process requirements that is essential in ultimately satisfying the customers demands. Over the past twenty years, Georgia Techs Center for Excellence in Rotorcraft Technology (CERT) has continuously focused on refining this IPPD approach within its rotorcraft design course by using the annual American Helicopter Society (AHS) Student Design Competition as the design requirement catalyst. Despite this extensive experience, however, the documentation of this preliminary rotorcraft design approach has become out of date or insufficient in addressing a modern IPPD methodology.
In no design discipline is this need for updated documentation more prevalent than in propulsion system design, specifically in the area of gas turbine technology. From an academic perspective, the vast majority of current propulsion system design resources are focused on fixed-wing applications with very limited reference to the use of turboshaft engines. Additionally, most rotorcraft design resources are centered on aerodynamic considerations and largely overlook propulsion system integration. This research effort is aimed at bridging this information gap by developing a preliminary turboshaft engine design methodology that is applicable to a wide range of potential rotorcraft propulsion system design problems. The preliminary engine design process begins by defining the design space through analysis of the initial performance and mission requirements dictated in a given request for proposal (RFP). Engine cycle selection is then completed using tools such as GasTurb and the NASA Engine Performance Program (NEPP) to conduct thorough parametric and engine performance analysis. Basic engine component design considerations are highlighted to facilitate configuration trade studies and to generate more detailed engine performance and geometric data. Throughout this approach, a comprehensive engine design case study is incorporated based on a two-place, turbine training helicopter known as the Georgia Tech Generic Helicopter (GTGH). This example serves as a consistent propulsion system design reference highlighting the level of integration and detail required for each step of the preliminary turboshaft engine design methodology.
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Roberts, James W. "Further calculations of the performance of turbofan engines incorporating a wave rotor." Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA240867.
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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 1990.Thesis Advisor(s): Shreeve, Raymond P. Second Reader: Hobson, Garth V. "September 1990." Description based on title screen as viewed on December 18, 2009. DTIC Descriptor(s): Rotors, Turbofan Engines, Waves, Gases, Pressure, Ratios, Computer Programs, Cycles. DTIC Identifier(s): Wave Rotors, Rotors, Waves, Theses. Author(s) subject terms: Turbofan Engines, Turbofan engines with a Wave Rotor. Includes bibliographical references (p. 95-96). Also available in print.
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Materano, Blanco Gilberto Ignacio. "Numerical modelling of pressure rise combustion for reducing emissions of future civil aircraft." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9259.
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This work assesses the feasibility of designing and implementing the wave rotor
(WR), the pulse detonation engine (PDE) and the internal combustion wave
rotor (ICWR) as part of novel Brayton cycles able to reduce emissions of future
aircraft. The design and evaluation processes are performed using the
simplified analytical solution of the devices as well as 1D-CFD models. A code
based on the finite volume method is built to predict the position and
dimensions of the slots for the WR and ICWR. The mass and momentum
equations are coupled through a modified SIMPLE algorithm to model
compressible flow. The code includes a novel tracking technique to ensure the
global mass balance. A code based on the method of characteristics is built to
predict the profiles of temperature, pressure and velocity at the discharge of the
PDE and the effect of the PDEs array when it operates as combustion chamber
of gas turbines. The detonation is modelled by using the NASA-CEA code as a
subroutine whilst the method of characteristics incorporates a model to capture
the throttling and non-throttling conditions obtained at the PDE's open end
during the transient process. A medium-sized engine for business jets is
selected to perform the evaluation that includes parameters such as specific
thrust, specific fuel consumption and efficiency of energy conversion. The ICWR
offers the best performance followed by the PDE; both options operate with a
low specific fuel consumption and higher specific thrust. The detonation in an
ICWR does not require an external source of energy, but the PDE array
designed is simple. The WR produced an increase in the turbine performance,
but not as high as the other two devices. These results enable the statement
that a pressure rise combustion process behaves better than pressure
exchangers for this size of gas turbine. Further attention must be given to the
NOx emission, since the detonation process is able to cause temperatures
above 2000 K while dilution air could be an important source of oxygen.
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Sureshkumar, Prathiban. "Near-field acoustic assessment of open rotor aero-engines." Thesis, University of Southampton, 2017. https://eprints.soton.ac.uk/417854/.
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The focus of this research, part sponsored by Rolls-Royce plc., is to both model and gain an understanding of the acoustics in the near-field of the open rotor aero-engine concept. The eventual aim of such work is to develop accurate and fast prediction models which can be used to optimise engine design and operation, so that the noise produced by the open rotor can be minimised to sit well under regulation noise levels. This work will also be used to help understand the results of important experimental testing of the open rotor. Finally, such work may be useful for understanding what cabin noise levels may be, which is a strong factor in passenger comfort and is therefore another consideration for the client. Outlined in this thesis are a number of tools and methods aimed at helping to predict the open rotor’s acoustic near-field in a fast and reliable fashion. As a primer, analytical models for the tonal noise of an open rotor in the free-field are first derived. The models are based on frequency domain methods, such as those proposed by Hanson in the 1980s. All models in this thesis may be used during engine development to make acoustic predictions at various operating conditions and gain insight into how certain rotor geometric features and operating conditions affect the generated noise level and propagation. Methods for projecting noise levels from the near-field to the far-field are also presented, which is useful when validating noise measurements from experiments. The effect of scattering from the open rotor centrebody and the effect of reverberation when contained in a closed test-section wind tunnel are also modelled. Centrebody scattering and tunnel reverberation have been shown from data analysis to have an impact on open rotor acoustic measurements. The analysis presented in this thesis has led to some novel mitigation techniques and suggestions for improved open rotor experiment design. Some limited comparisons to scaled open rotor experiments are provided, in order to validate the models and highlight further issues that would occur during real engine operation. The business case for and the environmental benefits of the open rotor are clear. Effcient operation is a key driver in the development of aircraft propulsion technologies, since it can significantly drive down operational costs and the open rotor aero-engine promises a step change improvement in fuel effciency. Another important objective during engine development is mitigating the generation of unwanted noise, in order to meet aircraft noise regulations.
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Frohnapfel, Dustin Joseph. "Experimental Investigation of Fan Rotor Response to Inlet Swirl Distortion." Thesis, Virginia Tech, 2016. http://hdl.handle.net/10919/71323.
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Next generation aircraft design focuses on highly integrated airframe/engine architectures that exploit advantages in system level efficiency and performance. One such design concept incorporates boundary layer ingestion which locates the turbofan engine inlet near enough to the lifting surface of the aircraft skin that the boundary layer is ingested and reenergized. This process reduces overall aircraft drag and associated required thrust, resulting in fuel savings and decreased emissions; however, boundary layer ingestion also creates unique challenges for the turbofan engines operating in less than optimal inlet flow conditions.
The engine inlet flow profiles predicted from boundary layer ingesting aircraft architectures contain complex distortions that affect the engine operability, durability, efficiency, and performance. One component of these complex distortion profiles is off-axial secondary flow, commonly referred to as swirl. As a means to investigate the interactions of swirl distortion with turbofan engines, an experiment was designed to measure distorted flow profiles in an operating turbofan research engine.
Three-dimensional flow properties were measured at discrete planes immediately upstream and immediately downstream of the fan rotor, isolating the component for analysis. Constant speed tests were conducted under clean and distorted test conditions. For clean tests, a straight cylindrical inlet duct was attached to the fan case; for distorted tests, a StreamVane swirl distortion generator was inserted into the inlet duct. The StreamVane was designed to induce a swirl distortion matching results of computation fluid dynamics models of a conceptual blended wing body aircraft at a plane upstream of the fan. The swirl distortion was then free to develop naturally within the inlet duct before being ingested by the engine.
Results from the investigation revealed that the generated swirl profile developed, mixed, and dissipated in the inlet duct upstream of the fan. Measurements immediately upstream of the fan rotor leading edge revealed 50% reduction in measured flow angle magnitudes along with evidence of fanwise vortex convection when compared to the StreamVane design profile. The upstream measurements also indicated large amounts of secondary flow entered the fan rotor. Measurements immediately downstream of the fan rotor trailing edge demonstrated that the fan processed the distortion and further reduced the intensity of the swirl; however, non-uniform secondary flow persisted at this plane. The downstream measurements confirmed that off-design conditions entered the fan exit guide vanes, likely contributing to cascading performance deficiencies in downstream components and reducing the performance of the propulsor system.Master of Science
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Shahriar, Hassan. "Structural design of the rotor and static structure of a microscale Rankine engine." Thesis, McGill University, 2009. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=66783.
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The goal of this thesis is to develop tools that will enable the design of the components of the Rankine micro-engine in order to satisfy performance and reliability requirements for high temperature operation. The Ashby approach was used to identify a set of candidate materials – zirconia, silica, titanium alloy, nickel-cobalt alloy, silicon carbide and silicon – for the insulating static structure and rotor. Subsequently, the stresses in, and deformations of, the insulating static structure were analyzed using analytical models and the method of finite elements. Subsequently, an idealized impact experiment was designed and performed to assess reliability of the rotor in the event of an accidental high-speed impact with the static sidewalls. The threshold velocity for initiating damage in alumina projectiles (balls) impacting on alumina targets (discs) was found to be 30 m/s, while the corresponding value for zirconia projectiles on alumina target was found to be around 65–70 m/s. These findings pave the way for developing detailed designs for the rotor and static sidewall of the Rankine micro-engine.L'objectif de cette thèse est de développer des outils qui permettront la conception de composants de moteur, afin de satisfaire les exigences de performance et de fiabilité de l'appareil dans des conditions extrêmes. Le méthode Ashby a été utilisée pour identifier un ensemble de matériaux - la zircone, la silice, de l'alliage de titane, de l'alliage nickel-cobalt, de silicium et de carbure de silicium – pour la structure statique isolante du rotor, ce qui révèle un compromis entre la performance, la fiabilité et la fabricabilité . Ultérieurement, les contraintes, et les déformations de la structure statique d'isolation ont été analysées par la méthode des éléments finis.Par la suite, une expérience idéalisée d'impact a été conçue et réalisée pour évaluer la fiabilité du rotor dans le cas d'un accident d'impact à grande vitesse avec la paroi latérale de la structure statique. La vitesse seuil d'ouverture des dommages dans des projectiles d'alumine (balles) un impact sur les objectifs de l'alumine (disques) a été retrouvé à 30 m/s, alors que le projectile en zircone sur la cible d'alumine a été jugé dans la région de 65 - 70 m/s. Ces résultats ouvrent la voie à la formulation de matériaux de conception pour le rotor et la paroi latérale statique du micro-moteur Rankine.
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Sykes, John Edward Hugh. "Investigation on non-linear phenomena in rotor-damper assemblies." Thesis, University of Southampton, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.314725.
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