Tato práce se zabývá problematikou aerodynamického zatížení statorových lopatek turbodmychadla s variabilní geometrií turbíny a jeho následnou optimalizací. Metody výpočtového modelování tekutin jsou aplikovány s využitím komerčního softwaru ANSYS CFX. Výpočtový model celého turbínového stupně je použit pro analýzu aerodynamického zatížení statorových lopatek v několika polohách a pro různé operační podmínky. Provedená byla detailní analýza vlivu rozložení tlaku v turbínové skříni, úhlu natočení lopatky, jakož i vlivu distančních pinů na aerodynamické zatížení. Následně bylo vyvinuto experimentální zařízení pro přímé měření aerodynamického momentu statorových lopatek s využitím testovacího zařízení s názvem Gas Stand. Toto zařízení spaluje zemní plyn a dokáže vytvořit velmi stabilní podmínky proudění při vysokých teplotách, což umožňuje vyloučit vliv pulzací plynu, vibrací motoru, jakož i vlivu řídící strategie motoru na měřenou veličinu. Výsledky experimentu jsou následně porovnány s vypočtenou hodnotou pomocí CFD modelu a je dosažená velmi dobrá shoda. Validovaný CFD model je následně zredukován s využitím podmínek cyklické symetrie na model jen jednoho segmentu statoru a rotoru. Umožňuje to výrazně zvýšit produktivitu simulací a prozkoumat několik návrhových parametrů statoru v celém rozsahu pohybu statorových lopatek. Provedená analýza citlivosti těchto parametrů položila výborný základ pro jejich následnou optimalizaci a ukázala významný potenciál několika z nich. Na základě analýzy požadavků na aerodynamické zatížení statorových lopatek byla následně vytvořena definice ideálního zatížení, která byla ustavena jako cíl pro jeho optimalizaci. Použitých bylo několik optimalizačních strategií s využitím metody analýzy působících silových vektorů a jejich výsledky byly následně zhodnoceny a porovnány z více aspektů. Výsledné optimalizované řešení bylo následně přepočteno pomocí modelu celého turbínového stupně, čímž se prokázali jeho výborné vlastnosti z hlediska aerodynamického zatížení a zvýšení účinnosti ve spodní části charakteristiky.

La mutation technologique du transport en général et aéronautique en particulier, engagée au niveau européen, conduit à une évolution vers des avions plus économiques et moins consommateurs de carburant. Ceci impacte fortement les systèmes de conditionnement d’air par une électrification partielle ne nécessitant plus de prélèvement d’air sur les réacteurs. Il est alors nécessaire d’assurer une large plage de débit à travers la turbine, élément de la turbomachine constituant le cœur du « pack » de conditionnement d’air, tout en fournissant le maximum de puissance possible sur l’ensemble de la plage. L’étage turbine classique ne peut pas assurer la plage de débit spécifiée. Il est donc remplacé par un étage turbine à section d’injection variable. Cet étage turbine doit fonctionner depuis la phase de maintenance au sol (faible débit, fort taux de détente) jusqu'en phase de croisière (fort débit, faible taux de détente), tout en assurant également son rôle sur les autres phases de vol et multiples cas de panne. La problématique est alors de concevoir une turbine dont la géométrie varie en fonctionnement et qui présente de très bons rendements sur une large plage de débit. Il est ainsi primordial de comprendre au préalable la complexité des écoulements pour ce type de géométrie, et comment le dispositif assurant la variation de section va influencer la topologie de l’écoulement dans l’étage turbine. En particulier, la présence de jeux dans les parties statiques de l’étage introduit une perturbation tourbillonnaire en amont du rotor. L’impact de cette perturbation sur l’écoulement principal, son interaction avec les écoulements secondaires, doit être détaillé. L’influence de la localisation de cette perturbation, de son intensité, doit être analysée, dans un contexte rendu très complexe par la variabilité de la géométrie. La compréhension des phénomènes mis en jeu responsables de la variation des performances dans l’étage turbine, permettra de définir une stratégie de dimensionnement à adopter. L’amélioration des performances de la turbine permettra ainsi de limiter la puissance demandée sur le moteur électrique afin de limiter la masse embarquée et donc la consommation de carburant. La méthodologie retenue pour aborder cette problématique, se décline en quatre volets. Un premier volet bibliographique pour s’approprier les phénomènes physiques liés à l’écoulement dans une turbine à géométrie variable et faire un état de l’art des solutions techniques existantes de géométrie variable des distributeurs de turbines centripètes. Un volet numérique dont l’objectif sera double. D'une part, de proposer une méthodologie de calcul robuste de prévision des performances et, d’autre part, de discriminer différentes options de dimensionnement dont la pertinence doit être démontrée sur l’ensemble de sa plage d’opérabilité. Un volet expérimental représentant la part principale de la thèse, consistera à mettre en place un module spécifique pour réaliser et analyser les essais pour des points de spécification représentatifs du fonctionnement de la turbine sur avion. Cela permettra de fournir une base de données d’analyse et de validation, et de quantifier les effets d’intégration. Ces études numérique et expérimentale seront conduites conjointement, afin que l’analyse de l‘écoulement profite de la complémentarité des deux approches. La dernière étape de cette étude a pour but la restitution des résultats obtenus et le savoir-faire vers l’industrie tant du point de vue de la prédiction des performances que de la méthodologie de dimensionnement des turbines à géométrie variable. / The technological mutation of transport in general and aeronautics in particular, engaged to the European level, leads to an evolution of more economical and fuel-efficient aircrafts. It strongly impacts the environmental control systems by a partial electrification which does not need an air bleeding on the engine anymore. Then it is necessary to insure a large output range through the turbine, element of the turbomachine which forms the heart of the air conditioning « pack », while providing the maximum amount of possible power on the whole range. The classical turbine stage cannot insure the specified output range. Then it is replaced by a variable geometry radial inflow turbine. This turbine stage has to function from the maintenance phase on the ground (weak output, strong expansion ratio) to the en route phase (strong output, weak expansion ratio). It also has to guarantee its role during the others phases of flight and in case of multiple failures power. So the problematic is to design a turbine such that its geometry varies in operation and adapt itself to the changing operating with the best possible efficiency on the widest possible range. Thus it is primordial to understand beforehand the complexity of flows for this kind of geometry, and how the variable geometry device affects the flow topology in the turbine stage. In particular, the presence of clearances in the static parts of the stage creates a vortex perturbation upstream from the rotor. The impact of this perturbation on the main flow, its interaction with secondary flows, must be detailed. The influence of the perturbation localisation, its intensity, must be analysed, in the complex variable geometry context. The understanding of phenomenon involved and responsible for the downgrade of performance in the turbine stage, will allow defining a specific strategy of design. The improvement of performance for the turbine will enable to restrict the required power on the electrical engine for limiting the on board weight, and then the fuel consumption. The selected methodology to broach this problematic, is divided into four parts. Firstly, a bibliographic part in order to appropriate physics phenomenon related to the flow in a variable geometry turbine will be conducted, together with a state of art about the different existing technological solutions. Secondly, some numerical simulations will be set to propose a methodology of robust calculations for performance prediction and, to discriminate different design options. The third step consists in an experimental phase representing the main work of the thesis. It will consist in the definition of a specific module instrumented for tests representative of the turbine on aircraft functioning. It will provide a database for analysing the flow and validating the numerical simulations, and to quantify the effects of integration. These numerical and experimental studies will be led jointly, such that the general analysis takes advantage of complementarity of both approaches. The last step of this study aims at conditioning the results achieved and the know-how for industrial application.

Tato práce se zabývá problematikou aerodynamického zatížení statorových lopatek turbodmychadla s variabilní geometrií turbíny a jeho následnou optimalizací. Metody výpočtového modelování tekutin jsou aplikovány s využitím komerčního softwaru ANSYS CFX. Výpočtový model celého turbínového stupně je použit pro analýzu aerodynamického zatížení statorových lopatek v několika polohách a pro různé operační podmínky. Provedená byla detailní analýza vlivu rozložení tlaku v turbínové skříni, úhlu natočení lopatky, jakož i vlivu distančních pinů na aerodynamické zatížení. Následně bylo vyvinuto experimentální zařízení pro přímé měření aerodynamického momentu statorových lopatek s využitím testovacího zařízení s názvem Gas Stand. Toto zařízení spaluje zemní plyn a dokáže vytvořit velmi stabilní podmínky proudění při vysokých teplotách, což umožňuje vyloučit vliv pulzací plynu, vibrací motoru, jakož i vlivu řídící strategie motoru na měřenou veličinu. Výsledky experimentu jsou následně porovnány s vypočtenou hodnotou pomocí CFD modelu a je dosažená velmi dobrá shoda. Validovaný CFD model je následně zredukován s využitím podmínek cyklické symetrie na model jen jednoho segmentu statoru a rotoru. Umožňuje to výrazně zvýšit produktivitu simulací a prozkoumat několik návrhových parametrů statoru v celém rozsahu pohybu statorových lopatek. Provedená analýza citlivosti těchto parametrů položila výborný základ pro jejich následnou optimalizaci a ukázala významný potenciál několika z nich. Na základě analýzy požadavků na aerodynamické zatížení statorových lopatek byla následně vytvořena definice ideálního zatížení, která byla ustavena jako cíl pro jeho optimalizaci. Použitých bylo několik optimalizačních strategií s využitím metody analýzy působících silových vektorů a jejich výsledky byly následně zhodnoceny a porovnány z více aspektů. Výsledné optimalizované řešení bylo následně přepočteno pomocí modelu celého turbínového stupně, čímž se prokázali jeho výborné vlastnosti z hlediska aerodynamického zatížení a zvýšení účinnosti ve spodní části charakteristiky.

The transition of the European energy grid to renewable energy sources is increasing the demand for back-up capacity with high flexibility. Current fossil fuel plants are continuously being forced into part load operation, where they are limited by pollution regulations that dictate their minimum environmental load, MEL. The power plants need to shut down when they no longer can comply to pollution regulations, but shutting down means that they can't act as quick back-up for the energy grid. Thus the EU project Turbo-Reflex aims to retrofit existing power plants in order to improve MEL by extending it to lower loads and, by doing so, meeting some of the back-up capacity that is needed. One method of improving MEL in a gas turbine power plants is reducing the mass flow from the compressor to the combustor. This study aims to investigate the stability and performance changes in a compressor as a function of intermediate mass extraction through bleeding lines. The study was made using a 2D throughflow model of a 15 stage axial compressor. Three different bleeding lines, positioned along the length of the compressor, were used for flow reduction. A design of experiments was made to get a structured data collection, combining different configurations of bleeding levels through the three lines, with up to 20% flow reduction. The influence of lowering the ambient temperature was also studied. Results detail the aerodynamic influence of intermediate mass extraction. The loading at the last stage increases with flow reduction, as evaluated by the diffusion factor, and stator 15 becomes the highest aerodynamically loaded position in the compressor. The increased loading is significantly dependent on the bleeding configuration, where upstream extraction is advantageous. The compressor power requirement has the same behavior, where extracting upstream has a 10% advantage. However, bleeding reduces efficiency, and in this regard it is better to use a bleed line further downstream. This combines into a trade off between these three parameters that needs to be made by the operator. Lowering the ambient temperature changes the interplay between these parameters. These research's results are part of the TURBO-REFLEX project, which has received funding from the European Union's Horizon 2020 research and innovation programme under grant agreement No. 764545.

<div>Bladeless fans are well known for their unique shape and efficient performance, which have a great impact on the fan industry. At present, there are few studies on the bladeless fan and the research on the improvement of fan design is a lack. Therefore, the study on the performance of the bladeless fan with different design is the main purpose of this thesis. </div><div>In the present study, a bladeless fan prototype is created and studied by numerical simulations. When characterizing the aerodynamic and aeroacoustic performances of the bladeless fan, the entire fan prototype, including wind channel, base, rotor and stator, is adopted; when investigating the influence of the wind channel's geometric parameters, only wind channel is considered in simulations. The influence of the slit width, the height of the cross-section, the slit location and the profile of the cross-section are studied. </div><div><br></div><div>It is found that the flow outside the bladeless fan consists of the air blown out from the wind channel and entrained from the back and side of the fan. The air entrained from the side is the main source of flow rate increase. As for the aeroacoustic performance, the rotor and stator inside the base are the predominated source of the noise generated by the bladeless fan. </div><div>The performances of the bladeless fan are very sensitive to the geometric details of the wind channel. The generated noise always increases as the wind strength improves. The slit width of the wind channel has the greatest impact. With the slit moves away from the leading edge, the wind produced by the bladeless fan becomes more powerful and the noise becomes louder. The cross-sectional height of 4cm has the best aerodynamic performance but the generated noise is a little larger than other designs. The profile of the cross-section shows insignificant influence on the performances. </div>

O presente trabalho busca através do uso de túnel de vento e de análises computacionais via CFD (Computacional Fluid Dynamics) avaliar o comportamento aerodinâmico que determinadas modificações nas arestas vivas de uma edificação retangular propiciam. No que tange a avaliação em túnel de vento, confeccionou-se modelos rígidos com diversas tomadas de pressão distribuídas nas fachadas dos modelos com o propósito de determinar a distribuição das isolinhas médias de pressão e os coeficientes aerodinâmicos. As simulações computacionais foram feitas a partir do uso do método de Taylor-Galerkin de 2 passos em sua forma explícita. Os modelos numéricos foram discretizados segundo o Método dos Elementos Finitos (MEF) utilizando a técnica de integração reduzida e controle de modos espúrios. A turbulência foi tratada utilizando o modelo de turbulência LES (Large Eddy Simulation), um simulador sintético de turbulência e a viscosidade turbulenta segundo a forma dinâmica. Ao final, concluiu-se que as modificações nas arestas vivas de um edifício alto, inicialmente retangular, são capazes de propiciar reduções significativas nas cargas de arrasto e laterais às quais a edificação estaria sujeita sem as modificações propostas. As isolinhas de pressão determinadas mostraram que há uma grande diferença na distribuição de pressões, sendo as modificações nas arestas capazes de diminuir os coeficientes de pressão experimentados pela estrutura. E que o uso integrado de ferramentas experimentais e numéricas pode propiciar um maior conhecimento e confiabilidade nos resultados obtidos na investigação da resposta aerodinâmica de uma estrutura. Além disso, através da comparação entre resultados experimentais e numéricos, viu-se que ambos apresentaram resultados próximos, demonstrando assim, a evolução dos métodos numéricos em avaliações de problemas de interesse da Engenharia do Vento. / The present work aims to evaluate the aerodynamics behavior that certain types of corner modifications in a rectangular building produce by using wind tunnel and computational analysis by CFD. Regarding the wind tunnel tests, rigid models were built using several pressure taps on their facades in order to determine the average pressure isolines distribution and the aerodynamic coefficients of the reduced models. Computational simulations were made using the two-step Taylor-Galerkin method in its explicit form. The numerical models were discretized according to the Finite Element Method (FEM) using the reduced integration technique and hourglassing control. The turbulence was treated using the Large Eddy Simulation (LES) methodology, a synthetic turbulence simulator and the turbulent viscosity according to the dynamic approach. At the end, it was concluded that the corner modifications in a tall building, initially rectangular, are able to produce significant reductions in drag and lift loads to which the building would be subject without the proposed modifications. The determined pressure isolines showed there is a great difference in the pressure distribution, being the corner modifications able to reduce the pressure coefficients experienced by the structure. And that the integrated use of numerical and experimental tools can provide greater knowledge and reliability in the results obtained in the investigation of the aerodynamic response of a structure. In addition, through the comparison between experimental and numerical results, it was observed that both presented close results, thus demonstrating the evolution of numerical methods in evaluations of problems of Wind Engineering interest.

No description available.

Most realistic fluid flow problems are characterised by high Reynolds numbers and complex boundaries. Over the last ten years, immersed boundary methods (IBM) that are able to cope with realistic geometries have been applied to Lattice- Boltzmann methods (LBM). These methods, however, have normally been applied to low Reynolds number problems. In the present work, an iterative direct forcing IBM has been successfully coupled with a multi-domain cascaded LBM in order to investigate viscous flows around rigid, moving and wilfully deformed boundaries at a wide range of Reynolds numbers. The iterative force-correction immersed boundary method of (Zhang et al., 2016) has been selected due to the improved accuracy of the computation, while the cascaded LB formulation is used due to its superior stability at high Reynolds numbers. The coupling is shown to improve both the stability and numerical accuracy of the solution. The resulting solver has been applied to viscous flow (up to a Reynolds number of 100000) passed a NACA-0012 airfoil at a 10 degree angle of attack. Good agreement with results obtained using a body-fitted Navier-Stokes solver has been obtained. At moving or deformable boundary applications, emphasis should be given on the influence of the internal mass on the computation of the aerodynamic forces, focusing on deforming boundary motions where the rigid body approximation is no longer valid. Both the rigid body and the internal Lagrangian points approximations are examined. The resulting solver has been applied to viscous flows around an in-line oscillating cylinder, a pitching foil, a plunging SD7003 airfoil and a plunging and flapping NACA-0014 airfoil. Good agreement with experimental results and other numerical schemes has been obtained. It is shown that the internal Lagrangian points approximation accurately captures the internal mass effects in linear and angular motions, as well as in deforming motions, at Reynolds numbers up to 4 • 104. Finally, an expanded higher-order immersed boundary method which addresses two major drawbacks of the conventional IBM will be presented. First, an expanded velocity profile scheme has been developed, in order to compensate for the discontinuities caused by the gradient of the velocity across the boundary. Second, a numerical method derived from the Navier-Stokes equations in order to correct the pressure distribution across the boundary has been examined. The resulting hybrid solver has been applied to viscous flows around stationary and oscillating cylinders and examined the hovering flight of elliptical wings at low Reynolds numbers. It is shown that the proposed scheme smoothly expands the velocity profile across the boundary and increases the accuracy of the immersed boundary method. In addition, the pressure correction algorithm correctly expands the pressure profile across the boundary leading to very accurate pressure coefficient values along the boundary surface. The proposed numerical schemes are shown to be very efficient in terms of computational cost. The majority of the presented results are obtained within a few hours of CPU time on a 2.8 GHz Intel Core i7 MacBook Pro computer with a 16GB memory.

The primary function of an automobile rear View Mirror is to provide the driver with a clear vision interpretation of all objects to the rear and side of the vehicle. The rear View Mirror is a bluff body and there are several problems associated with the rear View Mirror. These include buffeting, image distortion (due to aerodynamically induced and structural vibration), aerodynamically induced noise (due to cavities and gaps) and water and dirt accumulation on Mirror glass Surface. Due to excessive glass vibration, the rear View Mirror may not provide a clear image. Thus, vibrations of Mirror can severely impair the driver's vision and safety of the vehicle and its occupants. The rear View Mirrors are generally located close to the A-pillar region on the side window. A conical vortex forms on the side window close to A-pillar due to A-pillar geometry and the presence of side rear View Mirror and flow separation from it makes the airflow even more complex. The primary objective of this work is to study the aerodynamic pressures on Mirror Surface at Various speeds to determine the effects of aerodynamics on to Mirror vibration. Additionally, the Mirror was modified by Shrouding around the external periphery to determine the possibility of minimisation of aerodynamic pressure fluctuations and thereby vibration. The Shrouding length used for the analysis was of 24mm, 34mm and 44mm length. The mean and fluctuating pressures were measured using a production rear side View Mirror fitted to a ¼ quarter production passenger car in RMIT Industrial Wind Tunnel. The tests were also conducted in semi-isolation condition to understand influence of the A-pillar geometry. The mean and fluctuating pressures were converted into non-dimensional pressure coefficients (Cp and Cprms) and the frequency content of the fluctuating pressure was analysed. The results show that the fluctuating aerodynamic pressures are not uniformly distributed over an automobile Mirror Surface. The highest magnitude of fluctuating pressure for the standard Mirror was found at the central bottom part of the Mirror Surface. The highest magnitude of fluctuating pressure for the modified Mirror was found at the central top part of the Mirror Surface. As expected, the modification has significant effect on the magnitude of fluctuating pressure. The results show that an increase of Shrouding length reduces the magnitude of the fluctuating pressure. The frequency-based analysis was done to understand the energy characteristics of the flow, particularly to its phase, since it is the out of phase components that usually cause Mirror rotational vibration. The spectral analysis showed that the magnitude of the energy distribution reduces with increase of shrouding length throughout the frequency range. Flow visualisation was also used to supplement the pressure data. The effects of yaw angles were not included in this study, however, are thought to be worthy of further investigation. On road testing and the variation of mirror locations might have some effects on the fluctuating pressures. These need to be investigated in the future work. The quarter model used in this study was a car specific. However, for more generic results, a simplified model with variable geometry can be used in future study.

Delaying stall is always an attractive option in the aerospace industry. The major benefit of delaying stall is increased lift during takeoff and landings as well as during high angle of attack situations. Devices, such as fluidic oscillators, can be integrated into wing flaps to help delay the occurrence of stall by adding energized air to the airflow on the upper surface of the wing flap. The energized air from the oscillator allows the airflow to remain attached to the upper surface of the wing flap. The fluidic oscillator being integrated in this thesis is an active flow control device (AFC). One common method for integrating any device into a wing flap is to remove a section of the flap and mechanically secure the device. A current trend in the aerospace industry is the increased use of fiber-reinforced composites to replace traditional metal components on aircraft. The traditional methods of device integration cause additional complications when applied to composite components as compared to metal components. This thesis proposes an alternative method for integration of the AFC devices, which occurs before the fabrication of wing flaps is completed and they are attached to the aircraft wing. Seven design concepts are created to reduce the complications from using current methods of integration on composite wing flaps. The concepts are based on four design requirements: aerodynamics, manufacturing, maintenance, and structure. Four of the design concepts created are external designs, which place the AFC on the exterior surface of the wing flap in two types of grooved channels. The other three designs place the AFC inside the wing flap skin and are categorized as internal designs. In order for the air exiting the AFC to reach the upper surface of the wing flap, slots are created in the wing flap skin for the internal designs. Within each of the seven design concepts two design variants are created based on foam or ribbed core types. Prototypes were created for all of the external design AFC devices and the side inserted AFC and retaining pieces. Wing flap prototypes were created for the rounded groove straight AFC design, the semi-circular groove with straight AFC, and the side inserted AFC designs. The wing flaps were created using the VARTM process with a vertical layup for the external designs. The rounded groove and semi-circular groove prototypes each went through three generations of prototypes until an acceptable wing flap was created. The side inserted design utilized the lessons learned through each generation of the external design prototypes eliminating the need for multiple generations. The lessons learned through the prototyping process helped refine the designs and determine the ease of manufacturing to be used in the design evaluation. The evaluation of the designs is based on the four design requirements stated above. The assessment of the designs uses two levels of evaluation matrices to determine the most fitting design concept. As a result of the evaluation, all four of the external designs and one of the internal designs are eliminated. The two remaining internal designs' foam core and ribbed variants are compared to establish the final design selection. The vertically inserted AFC foam core design is the most fitting design concept for the integration of an AFC device into a composite wing flap.