This diploma thesis is focused at effect of time working hydrometric propeller between changes oil on measured velocity. From data what we have measured in laboratories of Department of water structures on the special small test track, we able to define size of measure bug, when we don´t change oil. One of outputs is graph of measure bug to measure time. Results of measure will be effect of oil.

A surface piercing propeller (SPP) is a propeller that is partially submerged in water and is considered a possible solution to high-speed vessels (greater than 50 knots) where cavitation plays a vital role due to its ever-increasing detrimental effects. Computational Fluid Dynamics (CFD) has become a more prevalent solution in recent years due to lower costs and the ability to evaluate varying setups. However, Computational Fluid Dynamics has had problems accurately solving the hydrodynamic loads for an SPP as recently as a few years ago. Accurately predicting these loads is of great importance because it will allow future simulations to add more effects such as cavitation, shaft inclination effects, multiple propellers, and fluid-structure interaction. Using FINE/Marine, a CFD software specifically designed for marine applications simulations with the 841-B SPP model and changing the Froude number (Fn) and advance coefficient (J), an in-depth validation process and extending upon previous results found when combining CFD and surface-piercing propellers was performed. Several cases between J = 0.6 to J = 1 and Fn = 2 to Fn = 6 are first performed to validate the models against experiments, then more complex features such as multiple propellers and shaft inclination angles were included to extend upon previous work of CFD for surface-piercing propellers. This analysis of the results suggests that CFD models could genuinely be validated against current experimental setups, and therefore more complex additions could also be made and with stronger accuracy than in previous years. / Master of Science / Using computers one can analyze the torque and thrust values of surface-piercing propellers(propeller that is only partially submerged) using commercially available software. This software takes inputs such as the speed of the water and the design of the propeller to evaluate the torque and thrust. A surface-piercing propeller operates in what is known as regimes. There are three of these and they are defined by a number known as the advance coefficient which is defined as the ratio of the boat's speed to the propeller speed. The higher this number the higher the boat speed is and the lower the number is the lower the boat speed. Testing the torque and thrust values accurately has not yet been performed using computers and would be of great value to companies and the government because it lowers the cost and time to create and test different propeller designs for their ships. In this thesis, these tests were performed and done so within a 5% accuracy in all experimental testing on this propeller model. Multiple propellers at once were tested as well as moving the shaft farther out of the water was tested to see how this would affect the overall performance. The results were promising in both of the situations listed, but more testing could be performed as well as adding more features such as cavitation and interaction with the hull.

Today, we see a renewed interest in aircraft with multiple propellers. To support conceptual design of these vehicles, one of the major needs is a fast and accurate method for estimating wing aerodynamic characteristics in the presence of multiple propellers. For the method to be effective, it must be easy to use, have rapid turnaround time and should be able to capture major wing–propeller interaction effects with sufficient accuracy. This research is primarily motivated by the need to assess the effectiveness of computational fluid dynamics (CFD) for simulating aerodynamic characteristics of wings with multiple propellers. The scope of the present research is limited to investigating the interaction between a single tractor propeller and a wing. This research aims to compare computational results from a Reynolds-Averaged Navier-Stokes (RANS) method, StarCCM+, and a vortex lattice method (VLM), VSP Aero. Two configurations that are analysed are 1) WIPP Configuration (Workshop for Integrated Propeller Prediction) 2) APROPOS Configuration. For WIPP, computational results are compared with measured lift and drag data for several angles of attack and Mach numbers. StarCCM+ results of wake flow field are compared with WIPP's wake survey data. For APROPOS, computed data for lift-to-drag ratio of the wing are compared with test data for multiple vertical and spanwise locations of the propeller. The results of the simulations are used to assess the effectiveness of the two CFD methods used in this research. / Master of Science / Today, we see a renewed interest in aircraft with multiple propellers due to an increasing demand for vehicles which fly short distances at low altitudes, be it flying taxis, delivery drones or small passenger aircrafts. To support conceptual design of vehicles, one of the major needs is a fast and accurate method for estimating wing aerodynamic characteristics in the presence of multiple propellers. For the method to be effective, it must be easy to use, have rapid turnaround time and should be able to capture major wing–propeller inter- action effects with sufficient accuracy. This research is primarily motivated by the need to assess the effectiveness of computational fluid dynamics (CFD) for simulating aerodynamic characteristics of wings with multiple propellers. Then only can we can take full advantage of the capabilities of the CFD methods and support design of emerging propeller driven air vehicles with an appropriate level of confidence. This research aims to compare high level methods with increasingly complex geometries and realistic models of physics like Reynolds Averaged Navier Stokes (RANS) and low level methods that rely on simplified geometry and simplified physics models like Vortex Lattice Methods (VLM). We will analyse multiple configurations and validate them against experi- mental data and thus assessing the effectiveness of the CFD models. This research investigates two configurations, 1) WIPP configuration 2) APROPOS configuration, for which experimental data is available. The results of the simulations are used to assess the effectiveness of the two CFD methods used in this research.

Les hélices sont connues pour leur avantage significatif en termes de rendement propulsif. Ces avantages se traduisent directement par une réduction de la consommation de carburant de sorte qu’elles connaissent aujourd’hui un regain d’intérêt. Actuellement, les avancées récentes en simulations numériques rendent possible d’appliquer l’optimisation multidisciplinaire au cas exigeant du design de pales d’hélice transsonique. Pour ces raisons, une méthode d’optimisation est développée, dans laquelle les objectifs de performance aérodynamique, aéroacoustique et aéroélastique sont en concurrence. Cette méthode est appliquée au design de pales d’hélice à haute vitesse et à simple rotation. L’optimisation s’appuie sur l’Evolution Différentielle Multi-Objectifs (Multi-Objective Differential Evolution - MODE). Cette technique est une des formes d’algorithme évolutionnaire qui mimique l’évolution naturelle des populations par le concours de la sélection, de la recombinaison et de l’éventuelle mutation de formes de pales, chacune d’elles étant représentée par un vecteur de variables (corde, angle de flèche, etc. . .). MODE offre l’avantage de considérer tous les objectifs en concurrence lors de la sélection des designs prometteurs au sein d’une population. Afin de garder le coût computationnel dans des limites acceptables, l’évaluation des performances des designs proposés est faite par une approche à deux niveaux. Un meta-modèle fournit les estimations de performance pour chaque design à un coût computationnel extrêmement faible alors que des codes d’analyse à haute fidélité calculent les performances précises à un coût nettement plus élevé. Pour préserver la précision des estimations, le meta-modèle est initialement entraîné sur une population composée à cet effet. L’entraînement est ensuite répété de temps à autres avec les performances haute fidélité de designs prometteurs. Différents outils à haute fidélité ont été développés et utilisés dans ce cadre. L’outil CFD exécute la simulation RANS stationnaire d’un seul passage d’entrepales pour une hélice isolée sans angle d’attaque dans un écoulement libre. Ces simulations délivrent les valeurs de performance aérodynamique. L’hélice complète est modélisée grâce à des conditions aux limites cycliques. Le modèle de turbulence k - ε est utilisé en combinaison avec un traitement adapté près des murs. Des conditions adiabatiques et sans glissement sont imposées sur le carénage et la surface de la pale tandis que la limite radiale de la section d’essais reproduit les effets d’un champ de pression lointain. Cette approche a prouvé sa robustesse et, par-dessus tout, sa précision puisque une correspondance acceptable avec des résultats expérimentaux est obtenue pour différentes conditions d’utilisation et un large éventail de formes de pales. De plus, l’indépendance par rapport au maillage est satisfaisante. Lors de l’analyse a posteriori des résultats aérodynamiques, le Sound Pressure Level (SPL) est calculé par l’outil aéroacoustique (CHA) pour le bruit tonal en différentes positions. La formulation 1A de Farassat est utilisée à cette fin. Cette formulation découle de l’équation non-homogène d’onde dérivée de l’analogie acoustique de Lighthill par Ffowcs Williams et Hawkings (FW-H). Elle bénéficie du découplage partiel des aspects aérodynamiques et aéroacoustiques en plus d’être particulièrement adaptée pour le calcul du bruit d’hélice. Le bruit d’épaisseur et le bruit de charge sont exprimés par des termes séparés dans le domaine temporel tandis que les quadripôles de l’équation de FW-H sont négligés. La surface de la pale est utilisée comme surface d’intégration et une nouvelle technique de troncation a été développée et appliquée pour circonvenir la singularité mathématique qui apparaît lorsque des parties de la pale ont des conditions soniques en termes de cinématique par rapport à l’observateur. Cette approche délivre des résultats fiables à un coût acceptable. [...] / Open rotors are known to have significant advantages in terms of propulsive efficiency. These advantages translate directly in reduced fuel burn so that they nowadays benefit from a surge of interest. At the same time, recent advances in numerical simulations make the application of multidisciplinary optimization for the demanding design of transonic propeller blades, an affordable option. Therefore, an optimization method in which the performance objectives of aerodynamics, aeroacoustics and aeroelasticity compete against each other, is developed and applied for the design of high-speed single-rotation propellers. The optimization is based on Multi-Objective Differential Evolution (MODE).This technique is a particular kind of evolutionary algorithm that mimics the natural evolution of populations by relying on the selection, recombination and eventually mutation of blade designs, each of them being represented by a vector of design variables (e.g. chord width, tip sweep, etc). MODE has the advantage of dealing concurrently with all the objectives in the selection of potentially promising designs among a population. In order to keep the computational cost within reasonable margins, the assessment of the performance of proposed designs is done in a two-level approach. A metamodel provides performance estimates for each proposed design at extremely low computational effort while high-fidelity analysis codes provide accurate performance values on some promising designs at much higher cost. To safeguard the accuracy of the estimates, the metamodel is initially trained on a population that is specifically assembled for that purpose. The training is repeated from time to time with the high-fidelity performance values of promising designs. Different high-fidelity tools have been developed and used for the assessment of performance.The CFD-tool performs steady RANS simulations of a single blade passage of the isolated propeller in free air under zero angle of attack. These simulations provide the aerodynamic performance values. The full propeller is modelled thanks to cyclic boundary conditions. The k - ε turbulence model is used in combination with wall treatment. Adiabatic no-slip wall conditions are imposed on the spinner and blade surfaces whereas the test-section radial boundary is reproducing the effects of a pressure far-field. This approach has proven its robustness and, above all, its accuracy as satisfactory agreement with experimental results has been found for different operating conditions over a wide range of blade shapes, as well as sufficient grid independency. In the post-processing of the aerodynamic results, the Sound Pressure Level (SPL)is computed for tonal noise at various observer locations by the aeroacoustic solver(CHA). Formulation 1A from Farassat is used for this purpose. This formulation is related to the inhomogeneous wave equation derived from Lighthill’s acoustic analogy by Ffowcs Williams and Hawkings (FW-H). It benefits from the partial decoupling of the acoustic and aerodynamic aspects and is particularly suited to compute the noise from propellers. The thickness noise and loading noise are expressed by separate equations in the time-domain whereas the quadrupole source term is dropped from the original FW-H equation. The blade surface is chosen as integration surface and a newly developed truncation technique is applied to circumvent the mathematical singularity arising when parts of the blade reach sonic conditions in terms of kinematics with respect to the observer. This approach delivers accurate values at acceptable computational cost. Besides, CSM-computations make use of a finite elements solver to compute the total mass of the blade as well as the stresses resulting from the centrifugal and aerodynamic forces. Considering the numerous possibilities to tailor the blade structure so that it properly takes on the stresses, only a simplified blade model is implemented. [...]

Approved for public release, distribution is unlimited / The extreme strain, strain rate and temperature gradients during Friction Stir Processing (FSP) render measurement of key parameters in the stir zone infeasible with common methods. The objective of this research was to separate the effects that temperature and deformation in an experimental study of the microstructure and mechanical properties of Ni-AL bronze (NAB). This was accomplished by subjecting as-cast NAB material to several isothermal annealing and quenching treatments as well as isothermal hot rolling processes. Sufficient material was generated to provide results and data for subsequent optical microscopy, tensile, & hardness tests. All results were then compared to similar data collected from previous works completed here at Naval Postgraduate School and with other DARPA FSP program participants. During the course of this work correlations were drawn between FSP material and the material subjected to isothermal hotworking, which may enhance our understanding of the roles that various FSP process parameters have on the microstructural transformation sequence within this material. The hot-rolling study conducted here suggests that FSP process parameters leading to severe deformation at temperatures between 950-1000 C in the NAB material provides high ductility (elongation approximately 28%) with moderate strengths. / Lieutenant, United States Coast Guard

Thesis (M.S.)--Air Force Institute of Technology, 2005. / "September 2005" Also available as a PDF file on the Air Force Institute of Technlogy website.

In this thesis, a numerical approach based on a potential flow method has been developed in order to simulate unsteady rotor/stator interaction, and to predict the unsteady performance of a propeller and its rudder. The method is first developed and tested in two-dimensions by using a boundary element method in which a front hydrofoil is moving downward, while a back hydrofoil is stationary. The wakes of the two hydrofoils are modeled by continuous dipole sheets and determined in time by applying a force free-condition on each wake surface. The wake/hydrofoil interaction is de-singularized by applying a numerical fence on the surface of the back hydrofoil. The viscous wake/hydrofoil interaction is considered by employing a viscous wake vorticity model on the rotor's wake surface. The present method is validated by comparison with analytical solutions, experimental data and by using the results from a commercial Reynolds Averaged Navier-Stokes (RANS) solver for the same set-up and conditions. The numerical approach is further extended to three-dimensions to predict the mutual interaction between a propeller and rudder. A fully unsteady wake alignment algorithm is implemented into a Vortex Lattice Method to simulate the unsteady propeller flow. The interaction between propeller and rudder is investigated in a fully unsteady manner, where a panel method is used to solve the flow around the rudder, and a vortex lattice method is used to solve the flow around the propeller. The interaction between a propeller and its rudder is considered in an iterative manner by solving the propeller and the rudder problems separately and by including the unsteady effects of one component on the other. The effect of the unsteady propeller-rudder interaction on the mean and on the unsteady propeller/rudder performance, including sheet cavitation on the rudder, is studied. / text

Dans le cadre du projet européen Clean Sky, Snecma construit un démonstrateur de Contra Rotating Open Rotor (CROR). La conception du système de régulation du moteur nécessite d'avoir connaissance du comportement aérodynamique de chacune des hélices du doublet. Les objectifs de cette thèse sont dans un premier temps de comprendre les interactions entre les différents éléments constitutifs d'un CROR ayant un effet sur les performances des hélices, d'isoler leurs contributions respectives et dans un deuxième temps de développer un modèle prédictif des performances individuelles des hélices d'un CROR intégrable dans un environnement de calcul de cycles thermodynamiques. Pour cela, le comportement des hélices en doublet est rapproché de celui d'hélices isolées dont les effets macroscopiques sont bien connus. Des calculs Euler et NS3D ont servi de base pour proposer un couplage entre les hélices isolées permettant de retrouver le champ de vitesses induits entre les hélices d'un calcul doublet. Pour respecter les exigences de rapidité d'exécution et de robustesse numérique imposées par l’environnement de calcul de cycles thermodynamiques, les performances individuelles des hélices du doublet sont calculées à partir de champs hélice isolée. Une approche monodimensionnelle permet de calculer les vitesses induites propres des hélices à partir de la traction et de la puissance absorbée et une méthode pour estimer les vitesses induites mutuelles à partir des vitesses induites propres est donnée. Le calcul des performances individuelles des hélices d'un doublet contrarotatif est itératif. Cette méthode estime les performances avec une erreur relative inférieure à 5%. Elle est utilisée dans le développement du système de régulation du démonstrateur CROR SAGE2. / Within the scope of the European research project Clean Sky, Snecma builds a ground demonstrator of the concept engine Contra Rotating Open Rotor (CROR). Engine control system design requires knowing how each propeller will behave aerodynamically under the interaction of each other. The aim of this work is to design a predictive model of contra rotating propeller individual performance fitting in a thermodynamic cycle calculation environment. A coupling is proposed in order to represent the dual propellers thanks to isolated propeller behavior. It has been shown that by matching the isolated propellers thrust and torque to the doublet values, the good values of mutual induced velocities can be found. Hence contra rotating propellers individual performance can be reached with a good variation in parameters. In addition to that, in order to meet withthermodynamic cycle calculation environment requirements of rapidity and numerical robustness, performance is calculated from pre-generated propeller maps. One-dimensional approach is used to calculate mutual induced velocities from propellers thrust and torque. Contra rotating propellers individual performance calculation is an iterative process. The method developed gives the performance within a 5% relative error margin and is currently used for the design of the ground demonstrator control system.

Micron scale robots going inside our body and curing various ailments is a technolog¬ical dream that easily captures our imagination. However, with the advent of novel nanofabrication and nanocharacterization tools there has been a surge in the research in this field over the last decade. In order to achieve locomotion (swim) at these small length scales, special strategies need to be adopted, that is able to overcome the large viscous damping that these microbots have to face while moving in the various bod¬ily fluids. Thus researchers have looked into the swimming strategies found in nature like that of bacteria like E.coli found in our gut or spermatozoa in the reproductive mucus. Biomimetic swimmers that replicate the motion of these small microorganisms hold tremendous promise in a host of biomedical applications like targeted drug delivery, microsurgery, biochemical sensing and disease diagnosis. In one such method of swimming at very low Reynolds numbers, a micron scale helix has been fabricated and rendered magnetic by putting a magnetic material on it. Small rotating magnetic fields could be used then to rotate the helix, which translated as a result of the intrinsic translation rotation coupling in a helix. The present work focussed on the development of such a system of nanopropellers, a few microns in length, the characterization of its dynamics and velocity fluctuations originating from thermal noise. The work has also showed a possible application of the nanopropellers in microrheology where it could be used as a new tool to measure the rheological characteristics of a complex heterogeneous environment with very high spatial and temporal resolutions. A generalized study of the dynamics of these propellers under a rotating field, has showed the existence of a variety of different dynamical configurations. Rigid body dynamics simulations have been carried out to understand the behaviour. Significant amount of insight has been gained by solving the equations of motion of the object analytically and it has helped to obtain a complete understanding, along with providing closed form expressions of the various characteristics frequencies and parameters that has defined the motion. A study of the velocity fluctuations of these chiral nanopropellers has been carried out, where the nearby wall of the microfluidic cell was found to have a dominant effect on the fluctuations. The wall has been found to enhance the average level of fluctuations apart from bringing in significant non Gaussian effects. The experimentally obtained fluctuations has been corroborated by a simulation in which a time evolution study of the governing 3D Langevin dynamics equations has been done. A closer look at the various sources of velocity fluctuations and a causality study thereof has brought out a minimum length scale below which helical propulsion has become impractical to achieve because of the increased effect of the orientational fluctuations of the propeller at those small length scales. An interesting bistable dynamics of the propeller has been observed under certain experimental conditions, in which the propeller randomly switched between the different dynamical states. This defied common sense because of the inherent deterministic nature of the governing Stokes equation. Rigid body dynamics simulations and stability analysis has shown the existence of time scales in which two different dynamical states of the propeller have become stable. Thus the intrinsic dynamics of the system has been found to be the reason behind the bistable behaviour, randomness being brought about by the thermal fluctuations present in the system. Finally, in a novel application of the propellers, they have been demonstrated as a tool for microrheological mapping in a complex fluidic environment. The studies done in this work have helped to develop this method of active microrheology in which the measurement times are orders of magnitude smaller than its existing counterparts.

This diploma thesis serves as a constructional study of an axial pump with a tandem arrangement of impellers. It may also be perceived as proposal of possible constructional variants that could be used as cardiac replacements. The thesis offers several conceptual variants, while the selected ones are elaborated in detail. Drawing documentation and 3D models are included in the attachment. The components were dimensioned according to the parameters necessary for proper heart function.