Efficient analysis and storage of data is an integral but often challenging task when working with computation fluid dynamics mainly due to the amount of data it can output. Methods centered around the proper orthogonal decomposition were used to analyze, compress, and model various simulation cases. Two different high-fidelity, time-accurate turbomachinery simulations were investigated to show various applications of the analysis techniques. The first turbomachinery example was used to illustrate the extraction of turbulent coherent structures such as traversing shocks, vortex shedding, and wake variation from deswirler and rotor blade passages. Using only the most dominant modes, flow fields were reconstructed and analyzed for error. The reconstructions reproduced the general dynamics within the flow well, but failed to fully resolve shock fronts and smaller vortices. By decomposing the domain into smaller, independent pieces, reconstruction error was reduced by up to 63 percent. A new method of data compression that combined an image compression algorithm and the proper orthogonal decomposition was used to store the reconstructions of the flow field, increasing data compression ratios by a factor of 40.The second turbomachinery simulation studied was a three-stage fan with inlet total pressure distortion. Both the snapshot and repeating geometry methods were used to characterize structures of static pressure fluctuation within the blade passages of the third rotor blade row. Modal coefficients filtered by frequencies relating to the inlet distortion pattern were used to produce reconstructions of the pressure field solely dependent on the inlet boundary condition. A hybrid proper orthogonal decomposition method was proposed to limit burdens on computational resources while providing high temporal resolution analysis.Parametric reduced order models were created from large databases of transient and steady conjugate heat transfer and airfoil simulations. Performance of the models were found to depend heavily on the range of the parameters varied as well as the number of simulations used to traverse that range. The heat transfer models gave excellent predictions for temperature profiles in heated solids for ambitious parameter ranges. Model development for the airfoil case showed that accuracy was highly dependent on modal truncation. The flow fields were predicted very well, especially outside the boundary layer region of the flow.

This thesis describes a novel new method, termed the Tangent-Line-Chord (TLC) method, that can be used to more efficiently model creep deformation dominated by the tertiary regime. Creep deformation is a widespread mechanical mode of failure found in high-stress and temperature mechanical systems. To accurately simulate creep and its effect on structures, researchers utilize finite element analysis (FEA). General purpose FEA packages require extensive amounts of time and computer resources to simulate creep softening in components because of the large deformation rates that continuously evolve. The goal of this research is to employ multi-regime creep models, such as the Kachanov-Rabotnov model, to determine a set of equations that will allow creep to be simulated using as few iterations as possible. The key outcome is the freeing up of computational resources and the saving of time. Because both the number of equations and the value of material constants within the model change depending on the approach used, programming software will be utilized to automate this analytical process. The materials being considered in this research are mainly generic Ni-based superalloys, as they exhibit creep responses that are dominated by secondary and tertiary creep.

[ES] El interés en reducir el peso y resistencia aerodinámica de vehículos y en desarrollar fuentes de energía renovables se ha incrementado debido a la compleja situación ambiental y los requerimientos legales para reducir las emisiones de contaminantes y el consumo de combustibles. La industria aeronáutica ha propuesto nuevos diseños que integren conceptos como alas de alto alargamiento y materiales con elevada resistencia específica, como los materiales compuestos. Por su parte, conceptos similares se emplean en la generación de energía eólica. El radio de las palas de las turbinas eólicas se incrementa paulatinamente, siendo un ejemplo muy claro las grandes instalaciones off-shore. El uso de estructuras más alargadas y ligeras provoca mayor deformación debida a las cargas aerodinámicas. Este fenómeno se conoce como aeroelasticidad y combina los efectos de las cargas aerodinámicas, los efectos inerciales y las tensiones internas de la estructura. La combinación de las cargas anteriores provoca fenómenos de amortiguamiento de las vibraciones, o por el contrario, inestabilidades aeroelásticas. Diferentes metodologías pueden ser empleadas para simular los fenómenos aeroelásticos. La metodología más extendida para la simulación de las ecuaciones elásticas del sólido es la conocida como análisis de elementos finitos. Respecto a las ecuaciones de conservación del fluido, la mecánica de fluidos computacional es la herramienta de resolución para un problema arbitrario. La combinación de las metodologías anteriores puede ser empleada para el cálculo de fenómenos aeroelásticos. Sin embargo, el coste computacional de estas simulaciones es inasumible en la mayoría de casos de aplicación. Se requiere una metodología nueva capaz de reducir el coste de cálculo. Este trabajo se centra en el desarrollo de modelos de orden reducido que permitan resolver el problema acoplado sin pérdidas sustanciales de precisión. En primer lugar, la estructura tridimensional se reduce a una sección equivalente que reproduzca la física del sólido original. La sección equivalente se acopla con dos modelos aerodinámicos: simulaciones de mecánica de fluidos computacional y un modelo reducido basado en redes neuronales. Ambos modelos presentan elevada precisión respecto a las simulaciones tridimensionales. Sin embargo, algunos efectos como los efectos aerodinámicos tridimensionales, las distribuciones de carga aerodinámica, la presencia de materiales ortotrópicos y los acoplamientos estructurales no pueden ser simulados. Con el objetivo de resolver los limitantes del modelo anterior, se propone un segundo modelo de orden reducido. En este caso se trata de un algoritmo basado en elementos de viga. El algoritmo se diseña para ser capaz de incluir el cálculo de materiales ortotrópicos y diferentes tipos de problemas aeroelásticos. Inicialmente, se emplea el software para determinar su precisión en el cálculo de una viga de material compuesto y sección rectangular. Estos resultados se validan con las simulaciones tridimensionales. De este modo se demuestra la capacidad de la herramienta computacional para predecir las inestabilidades y los efectos de acoplamiento estructural provocados por la orientación de las fibras. Posteriormente, el algoritmo se emplea en la simulación de turbinas eólicas, mejorando los rangos de operación de las palas sin que ello suponga una penalización desde el punto de vista del peso de la misma. Finalmente, un ala basada en una estructura de membrana resistente es simulada. El cálculo obtiene una gran precisión en la predicción de la velocidad de flameo respecto a la simulación acoplada, siendo la única limitación del modelo la predicción de la distorsión de la membrana. El trabajo presente un conjunto de modelos de orden reducido que permiten disminuir el coste computacional de las simulaciones aeroelásticas en órdenes de magnitud. También, se proporcionan directrices para la selección del modelo reducido apropiado para los casos de interés. / [CA] L'interès a reduir el pes i la resistència aerodinàmica dels vehicles i a desenvolupar fonts d'energia renovables s'ha incrementat a causa de la complexa situació ambiental i els requeriments legals per a reduir les emissions de contaminants i el consum de combustibles. La indústria aeronàutica ha proposat nous dissenys que integren conceptes com ales d'alt allargament i materials amb elevada resistència específica, com ara els materials compostos. Per la seua banda, conceptes similars es fan servir en la generació d'energia eòlica. El radi de les pales de les turbines eòliques s'incrementa progresivament, sent un exemple molt clar les grans instal·lacions off-shore. L'ús d'estructures més allargades i lleugeres provoca més deformació deguda a les càrregues aerodinàmiques. Aquest fenomen es coneix com a aeroelasticitat i combina els efectes de les càrregues aerodinàmiques, els efectes inercials i les tensions internes de l'estructura. La combinació de les càrregues anteriors provoca fenòmens d'esmorteïment de les vibracions, o per contra, inestabilitats aeroelàstiques. Diferents metodologies poden ser emprades per simular els fenòmens aeroelàstics. La metodologia més estesa per a la simulació de les equacions elàstiques del sòlid és la coneguda com a anàlisi d'elements finits. Pel que fa a les equacions de conservació del fluid, la mecànica de fluids computacional és l'eina de resolució per a un problema arbitrari. La combinació de les metodologies anteriors pot ser emprada per al càlcul de fenòmens aeroelàstics. Tot i això, el cost computacional d'aquestes simulacions és inassumible en la majoria de casos d'aplicació. Cal una metodologia nova capaç de reduir el cost de càlcul. Aquest treball se centra en el desenvolupament de models d'ordre reduït que permeten resoldre el problema acoblat sense pèrdues substancials de precisió. En primer lloc, l'estructura tridimensional es reduix a una secció equivalent que reproduixca la física del sòlid original. La secció equivalent s'acobla amb dos models aerodinàmics. El primer empra les forces aerodinàmiques obtingudes mitjançant simulacions de mecànica de fluids computacional. Posteriorment es fa servir un model reduït basat en xarxes neuronals. Tots dos models presenten elevada precisió respecte a les simulacions tridimensionals. No obstant això, alguns efectes com ara els efectes aerodinàmics tridimensionals, les distribucions de càrrega aerodinàmica, la presència de materials ortotròpics i els acoblaments estructurals no poden ser simulats. Amb l'objectiu de resoldre els limitants del model anterior, es proposa un segon model dordre reduït. En aquest cas és un algorisme basat en elements de biga. L'algorisme es dissenya per ser capaç d'incloure el càlcul de materials ortotròpics i diferents tipus de problemes aeroelàstics. Inicialment, s'empra el programari per determinar-ne la precisió en el càlcul d'una biga de material compost i secció rectangular. Aquests resultats es validen amb les simulacions tridimensionals. D'aquesta manera, es demostra la capacitat de l'eina computacional per predir les inestabilitats i els efectes d'acoblament estructural provocats per l'orientació de les fibres. Posteriorment, l'algorisme s'empra en la simulació de turbines eòliques, millorant els rangs d'operació de les pales sense que això suposi una penalització des del punt de vista del pes. Finalment, una ala basada en una estructura de membrana resistent és simulada. El càlcul obté una gran precisió en la predicció de la velocitat de flameig respecte a la simulació acoblada, i l'única limitació del model és la predicció de la distorsió de la membrana. El treball presenta un conjunt de models reduïts que permeten disminuir el cost computacional de les simulacions aeroelàstiques en ordres de magnitud. També es proporcionen directrius per a la selecció del model reduït adequat per als casos d'interès. / [EN] The complex environmental situation and the legal requirements for decreasing pollutant emissions and fuel consumption have increased the interest in reducing the empty weight and drag of vehicles and developing renewable energy sources. Due to the former, the aviation industry has proposed new designs integrating high strength-to-weight ratios, such as composite materials and higher aspect ratio wings. These increases in aspect ratio have also been applied to wind energy generation. The rotors of wind turbines are increasing their diameters in recent years: a clear example is the massive off-shore facilities. Using larger and lightweight structures increases the effects of the aerodynamic loads on structural deformation. Structural dynamics are strongly connected to the air-structure interaction. This phenomenon, called aeroelasticity, combines the effect of the external aerodynamic loads, the inertial forces, and the internal elastic stress of the structure. The complex combination of all the previous effects may damp the vibrations of the structure, or on the contrary, they could increase their amplitude, resulting in an unstable phenomenon. The simulation of the aeroelastic phenomena can be performed using different approaches. The well-known finite element analysis is the most extended methodology for solving solid elastic equations. Regarding fluid conservation equations, computational fluid dynamics is the principal tool for resolving general aerodynamic problems. The aeroelastic simulations can be calculated by combining the previous algorithms. Nevertheless, the computational cost of these methodologies is excessive for a general engineering case. Therefore, new methodologies are required. This work focuses on developing aeroelastic reduced-order models that compute the coupled phenomena without substantial accuracy losses. Initially, the complete three-dimensional structure is reduced to an equivalent section that reproduces the structure. The equivalent structural section is coupled with two aerodynamic models. The first one uses the forces calculated with aeroelastic computational fluid dynamics. Then, a surrogate model based on artificial neural networks is combined with the equivalent section. Both models show accurate agreement compared to the complete three-dimensional simulations in predicting unstable velocity. However, the three-dimensional aerodynamic effects, load distribution, orthotropic materials, and structural couplings cannot be considered. In order to solve the previous limitations, a reduced-order model based on a beam element solver is proposed. The algorithm is designed to consider a general orthotropic material and different typologies of aeroelastic problems. Initially, the software is proven to simulate accurately a squared cross-section composite material beam. The results are validated with the complete three-dimensional simulations, demonstrating the capabilities of the tool for predicting the instabilities and the effects of the fiber orientations. Then, the algorithm is used for simulating a wind turbine blade, and the algorithm results are used to improve the operation range of the blades without weight penalties. Finally, a resistant membrane wing is simulated, obtaining high accuracy in the prediction of the flutter velocity compared with the complete coupled simulation. In addition, the only limitation of the model is the prediction of the membrane distortion. The work presents a set of reduced-order models that allow for reducing the computational cost of the aeroelastic simulations by orders of magnitude. In addition, a decision pattern is provided for selecting the appropriate algorithm for the interest problem. / This thesis have been funded by Spanish Ministry of Science, Innovation and University through the University Faculty Training (FPU) program with reference FPU19/02201. / Cremades Botella, A. (2023). Fluid-structure interaction with the application to the non-linear aeroelastic phenomena [Tesis doctoral]. Universitat Politècnica de València. https://doi.org/10.4995/Thesis/10251/199249

<p dir="ltr">New system-level codes are being developed for advanced reactors for safety analysis and licensing purposes. Thermal-hydraulics of advanced reactors is a challenging problem due to complex flow scenarios assisted by free jets and stratified flows that lead to turbulent mixing. For these reasons, the 0D or 1D models used for reactor plena in traditional safety analysis codes like RELAP cannot capture the physics accurately and introduce a large degree of modeling uncertainty. System-level calculation codes based on the advection-diffusion equation neglect turbulent fluctuations. These fluctuations are extremely important as they introduce higher-order moments, which are responsible for vortex stretching and the passage of energy to smaller scales. Alternatively, extremely detailed simulations with velocity coupling from the Navier-Stokes equations are able to capture turbulence effects accurately using DNS. These solutions are accurate because they resolve the flow into the smallest possible length and time scales (Kolmogorov scale) important to the flow, which makes DNS computationally expensive for simple geometries and impossible at the system level.</p><p dir="ltr">The flow field can be described through a reduced-order model using the principles of statistical mechanics. Statistical mechanics-based methods provide a method for extracting statistics from data and modeling that data using easily represented differential equations. The Kramers-Moyal (KM) expansion method can be used as a subgrid-scale (SGS) closure for solving the momentum equation. The stochastic Burgers equation is solved using DNS, and the DNS solutions are used to calculate the KM coefficients, which are then implemented as an SGS closure model. The KM method outperforms traditional methods in capturing the multi-scale behavior of Burgers turbulence. The functional dependencies of the KM coefficients are also uniform for several boundary conditions, meaning the closure model can be extended to multiple flow scenarios. </p><p dir="ltr">For the case of the Navier-Stokes equations, each particle trajectory tends to follow some scaling law. Kolmogorov hypothesized that the flow velocity field follows a -5/3 scaling in the inertial region where Markovian characteristics can be invoked to model the interaction between eddies of adjacent sizes. This law holds true in the inertial region where the flow is Markovian. For scalar turbulence, the scaling laws are affected by thermal diffusion. If a fluid has a Prandtl number close to one, the thermal behavior is dominated by momentum, so the spectra for velocity and temperature are similar. For small Prandtl number fluids, such as liquid metals, the thermal diffusion dominates the lower scales and the slope of the spectrum shifts from the -5/3 slope to a -3 slope, also called the Batchelor region. System-level thermal hydraulics codes need to be able to capture these behaviors for a range of Prandtl number fluids. The KM-based model can also be used as a surrogate for velocity or temperature fluctuations in scalar turbulence. Using DNS solutions for turbulent channel flow, the KM model is used to provide a surrogate for temperature and velocity signals at different wall locations in the channel for Pr = 0.004, Pr = 0.025, and Pr = 0.71. The KM surrogate matches well for all wall locations, but is not able to capture the viscous dissipation in the velocity signal, or the thermal dissipation in the low Prandtl number cases. The dissipation can be captured by implementing a Gaussian filter.</p><p dir="ltr">Statistical mechanics-based methods are not limited to modeling turbulence in a reactor. Renewable power generation, such as wind, can be modeled using the Ornstein-Uhlenbeck (OU) method, which allows the long-term trends and short-term fluctuations of wind power to be decoupled. This allows for large fluctuations in wind power to be scaled down to a level that a reactor can accommodate safely. </p><p dir="ltr">Since statistical mechanics methods are based in physics, the calculated coefficients provide some information about the inputted signal. In a high-temperature gas-cooled reactor, strong heating can cause flow that is expected to be turbulent to show laminar characteristics. This laminarization results in reduced heat removal. The KM coefficients can be used to classify the laminarization from probed velocity signals more effectively than traditional statistical analyses.</p>

No description available.

Le développement de la fabrication additive permet d'élaborer des pièces de forme extrêmement complexes, en particulier des structures alvéolaires ou "lattices", où l'allégement est recherché. Toutefois, cette technologie, en très forte croissance dans de nombreux secteurs d'activités, n'est pas encore totalement mature, ce qui ne facilite pas les corrélations entre les mesures expérimentales et les simulations déterministes. Afin de prendre en compte les variations de comportement, les approches multiparamétriques sont, de nos jours, des solutions pour tendre vers des conceptions fiables et robustes. L'objectif de cette thèse est d'intégrer des incertitudes matérielles et géométriques, quantifiées expérimentalement, dans des analyses de flambement. Pour y parvenir, nous avons, dans un premier temps, évalué différentes méthodes de substitution, basées sur des régressions et corrélations, et différentes réductions de modèles afin de réduire les temps de calcul prohibitifs. Les projections utilisent des modes issus soit de la décomposition orthogonale aux valeurs propres, soit de développements homotopiques ou encore des développements de Taylor. Dans un second temps, le modèle mathématique, ainsi créé, est exploité dans des analyses ensemblistes et probabilistes pour estimer les évolutions de la charge critique de flambement de structures lattices. / The development of additive manufacturing allows structures with highly complex shapes to be produced. Complex lattice shapes are particularly interesting in the context of lightweight structures. However, although the use of this technology is growing in numerous engineering domains, this one is not enough matured and the correlations between the experimental data and deterministic simulations are not obvious. To take into account observed variations of behavior, multiparametric approaches are nowadays efficient solutions to tend to robust and reliable designs. The aim of this thesis is to integrate material and geometric uncertainty, experimentally quantified, in buckling analyses. To achieve this objective, different surrogate models, based on regression and correlation techniques as well as different reduced order models have been first evaluated to reduce the prohibitive computational time. The selected projections rely on modes calculated either from Proper Orthogonal Decomposition, from homotopy developments or from Taylor series expansion. Second, the proposed mathematical model is integrated in fuzzy and probabilistic analyses to estimate the evolution of the critical buckling load for lattice structures.

Many companies have a large collection of different model variants and results. Hexagon's (formerly MSC Software) software Odyssee helps to find out what information is contained in this data. New calculations can sometimes be avoided because the results for new parameter combinations can be predicted from the existing calculations. This is particularly interesting for non-linear or large models with long run times. The software also helps when setting up new DOEs and offers a variety of options for statistical displays. In the lecture, the number-based and image-based methods are compared. / Viele Firmen können auf eine große Sammlung vorhandener Rechnungen für verschiedene Modellvarianten zurückgreifen. Die Software Odyssee von Hexagon (früher MSC Software) hilft herauszufinden, welche Informationen in diesen Daten stecken. Neue Rechnungen kann man sich teilweise ersparen, weil die Ergebnisse für neue Parameterkombinationen aus den vorhandenen Rechnungen vorhergesagt werden können. Dies ist besonders interessant für nichtlineare oder große Modelle mit langer Rechenzeit. Die Software hilft auch beim Aufsetzen neuer DOEs und bietet vielfältige Möglichkeiten für statistische Darstellungen. In dem Vortrag werden die zahlenbasierte und bildbasierte Methode gegenübergestellt.