Relevant bibliographies by topics / Rotor flows

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  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
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Academic literature on the topic 'Rotor flows'

Author: Grafiati
Published: 3 June 2025
Last updated: 13 July 2025

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Journal articles on the topic "Rotor flows"

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STATSENKO, V., O. BURMISTENKOV, and T. BILA. "DETERMINATION OF THE BULK MATERIALS PARTICLES DISTRIBUTION DURING MIXING IN THE CONTINUOUS ACTION CENTRIFUGAL MIXERS ROTOR." Herald of Khmelnytskyi National University. Technical sciences 281, no. 1 (2020): 238–44. http://dx.doi.org/10.31891/2307-5732-2020-281-1-238-244.

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The article presents the results of the bulk materials particles movement study in continuous centrifugal mixers with conical rotors. Mathematical models of particle motion in the rotor are developed. The systems of differential equations that describe the particles motion on the rotor bottom and side surface are given. Particle trajectories are shown. The effect of the particle flow initial position in the rotor on the particles distribution at the rotor exit is studied. A relationship is established between the particles distribution at the rotor exit and the mixture homogeneity, which was estimated using the coefficient of variation. The mathematical modelling results of a two-component mixture particles distribution under various initial motion conditions of these components are presented. Four variants of the mixture components movement inside the rotor are considered. The initial conditions for the particles motion differed in the initial components flows position at the rotor bottom, as well as in these flows number. For all cases, histograms of the particles distribution along the rotor outer edge with a 150 step were plotted. In all zones, the particles number of each mixture component was calculated and its percentage composition was determined. Based on the data obtained, the mixture homogeneity was determined. It was found that the mixture homogeneity increases with a decrease in the difference between the particles flows initial motion conditions in the rotor. It was also found that dividing the flows into parts increases the mixture uniformity.
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Frontin, Cory, Ganesh Vijayakumar, and Pietro Bortolotti. "Aerodynamic and production comparison of wind farms with downwind versus conventional upwind turbines." Journal of Physics: Conference Series 2767, no. 9 (2024): 092008. http://dx.doi.org/10.1088/1742-6596/2767/9/092008.

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Abstract Ever-increasing turbine scales and their associated logistical challenges have reignited questions about the performance of downwind rotor configurations. A particular potential benefit of downwind rotor configurations is the farm-scale power increase that may be conferred by tilt-driven downward wake entrainment and associated wake recovery. In this work, a comprehensive aerodynamic analysis is carried out to understand the mechanisms for wake entrainment and recovery across a spectrum of velocity and inflow alignment conditions on a small, structured farm in order to understand the impact of downwind rotors on farm production. The results show that the benefits demonstrated previously in the literature for downwind-rotor farms in aligned flows are fragile, and, outside of strong farm/flow alignment conditions, power production benefits for small farms with downwind rotor configurations are significantly if not completely mitigated by misalignment effects. The work indicates that farm-scale benefits for downwind rotors must be realized either from large-scale entrainment benefits, with more exotic farm arrangements that can take advantage of the aerodynamic effects, or from beneficial fatigue impacts from entrainment of less turbulent outer boundary layer flows.
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Hah, C., and A. J. Wennerstrom. "Three-Dimensional Flowfields Inside a Transonic Compressor With Swept Blades." Journal of Turbomachinery 113, no. 2 (1991): 241–50. http://dx.doi.org/10.1115/1.2929092.

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The concept of swept blades for a transonic or supersonic compressor was reconsidered by Wennerstrom in the early 1980s. Several transonic rotors designed with swept blades have shown very good aerodynamic efficiency. The improved performance of the rotor is believed to be due to reduced shock strength near the shroud and better distribution of secondary flows. A three-dimensional flowfield inside a transonic rotor with swept blades is analyzed in detail experimentally and numerically. A Reynolds-averaged Navier–Stokes equation is solved for the flow inside the rotor. The numerical solution is based on a high-order upwinding relaxation scheme, and a two-equation turbulence model with a low Reynolds number modification is used for the turbulence modeling. To predict flows near the shroud properly, the tip-clearance flow also must be properly calculated. The numerical results at three different operating conditions agree well with the available experimental data and reveal various interesting aspects of shock structure inside the rotor.
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Van Zante, Dale E., Anthony J. Strazisar, Jerry R. Wood, Michael D. Hathaway, and Theodore H. Okiishi. "Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors." Journal of Turbomachinery 122, no. 4 (1999): 733–42. http://dx.doi.org/10.1115/1.1314609.

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The tip clearance flows of transonic compressor rotors are important because they have a significant impact on rotor and stage performance. A wall-bounded shear layer formed by the relative motion between the overtip leakage flow and the shroud wall is found to have a major influence on the development of the tip clearance flow field. This shear layer, which has not been recognized by earlier investigators, impacts the stable operating range of the rotor. Simulation accuracy is dependent on the ability of the numerical code to resolve this layer. While numerical simulations of these flows are quite sophisticated, they are seldom verified through rigorous comparisons of numerical and measured data because these kinds of measurements are rare in the detail necessary to be useful in high-speed machines. In this paper we compare measured tip-clearance flow details (e.g., trajectory and radial extent) with corresponding data obtained from a numerical simulation. Laser-Doppler Velocimeter (LDV) measurements acquired in a transonic compressor rotor, NASA Rotor 35, are used. The tip clearance flow field of this transonic rotor is simulated using a Navier–Stokes turbomachinery solver that incorporates an advanced k–ε turbulence model derived for flows that are not in local equilibrium. A simple method is presented for determining when the wall-bounded shear layer is an important component of the tip clearance flow field. [S0889-504X(00)02504-6]
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Freitas, Felipe Augusto Lustosa Meireles, Ronaldo Barcelos e. Silva, Leonardo Da Rosa Schmidt, Silvana Maldaner, and Lucinéia Fabris. "Análise da potência mecânica de rotores de Savonius de mesma razão de aspecto." Ciência e Natura 42 (February 7, 2020): 33. http://dx.doi.org/10.5902/2179460x40635.

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An experimental performance study of Savonius small rotors is performed in this work. Two Savonius prototypes, two blades and the same aspect ratio, were constructed from vinyl polychloride and use different air flow. Experimental tests allowed the rotation speed of each rotor to be determined for different air flows. It is important to note that the average angular velocity of the smaller rotor is approximately fifty percent higher than the larger rotor. At the same time, the absorption torque on the rotor shaft was measured and the mechanical power of each Savonius wind turbine prototype was estimated. The main result was that wind turbines of the same aspect ratio have different performances.
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Redchyts, Dmytro, Koldo Portal-Porras, Serhii Tarasov, et al. "Aerodynamic Performance of Vertical-Axis Wind Turbines." Journal of Marine Science and Engineering 11, no. 7 (2023): 1367. http://dx.doi.org/10.3390/jmse11071367.

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The nonstationary separated incompressible flows around Darrieus and Savonius rotors of vertical-axis wind turbines were investigated through computational simulation using the Reynolds averaged Navier–Stokes equations and Spalart–Allmaras turbulence model. The implicit finite-volume algorithm, the basis of which was artificial compressibility method, was chosen to obtain the numerical solution. The series of computational and physical experiments for Darrieus rotors with varied numbers and shapes of blades were performed. The detailed visualization of the flow was presented. The turbulent flows surrounding the Darrieus and Savonius rotors were studied, and as a part of these investigations, the major phases of vortex progress were identified. For this purpose, three series of computer tests on the aerodynamic and power properties of Savonius rotors with two and three buckets were performed, and their results are also presented. The influence of tip-speed ratio, solidity, and Reynolds numbers on the power coefficients of the Darrieus and Savonius rotors was investigated. It has been demonstrated that increasing Reynolds number from 104 to 106 causes a rise in Darrieus rotors power coefficient from 0.15 up to 0.5. The maximum values of power coefficient are moved away from higher values of tip-speed ratio from 2 to 5 as a result of a decrease in Darrieus rotor solidity from 1.0 to 0.33. The greatest power coefficient for a Savonius rotor with two blades is 0.23 and for a Savonius rotor with three blades is 0.19.
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Koya, M., and S. Kotake. "Numerical Analysis of Fully Three-Dimensional Periodic Flows Through a Turbine Stage." Journal of Engineering for Gas Turbines and Power 107, no. 4 (1985): 945–52. http://dx.doi.org/10.1115/1.3239840.

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Fully three-dimensional periodic flows through a turbine stage of stator and rotor are studied numerically by solving time-dependent three-dimensional Euler equations with the finite-volume method. The phase relation of stator and rotor flows and the related blade-row interaction are accounted for in the time-space domain. The established method of numerical calculation makes a practical contribution to predict actual turbine flows through a turbine stage of stator and rotor which have an arbitrary number of blades.
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Arndt, N. "Blade Row Interaction in a Multistage Low-Pressure Turbine." Journal of Turbomachinery 115, no. 1 (1993): 137–46. http://dx.doi.org/10.1115/1.2929198.

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The objective of this work was to enhance the understanding of unsteady flow phenomena in multistage low-pressure turbines. For this purpose, hot-film probe measurements were made downstream of every rotor blade row of a five-stage low-pressure turbine. Rotor–rotor interaction and stator–rotor interaction were observed to have a profound influence on the flow through the low-pressure turbine. Interaction of rotors of different turbine stages occurred owing to the influence of the wakes shed by one rotor blade row upon the flow through the next downstream rotor blade row. This wake-induced rotor–rotor interaction resulted in strongly amplitude-modulated periodic and turbulent velocity fluctuations downstream of every rotor blade row with the exception of the most upstream one. Significantly different wake depths and turbulence levels measured downstream of every rotor blade row at different circumferential positions evidenced the effect of the circumferentially nonuniform stator exit flow upon the next downstream rotor blade row. Stator-rotor interaction also strongly influenced the overturning and the under-turning of the rotor wakes, caused by the rotor secondary flows, in the rotor endwall regions. Low rotor wake overturning and underturning, i.e., reduced rotor secondary flow influence, were observed to correlate well with low rotor wake turbulence levels.
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Kühnlein, Christian, Andreas Dörnbrack, and Martin Weissmann. "High-Resolution Doppler Lidar Observations of Transient Downslope Flows and Rotors." Monthly Weather Review 141, no. 10 (2013): 3257–72. http://dx.doi.org/10.1175/mwr-d-12-00260.1.

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Abstract The authors present observations of the temporal evolution of downslope windstorms with rotors and internal hydraulic jumps of unprecedented detail and spatiotemporal coverage. The observations were carried out by means of a coherent Doppler lidar in the lee of the southern Sierra Nevada range during the sixth intensive observational period of the Terrain-induced Rotor Experiment (T-REX) in 2006. Two representative flow regimes are analyzed and juxtaposed in this paper. The first case shows pulses of high-momentum air that propagate eastward through the valley with an internal hydraulic jump on the leading edge. The region downstream of the transient internal hydraulic jump is characterized by turbulence but no coherent rotor circulation was observed. During the second case, the strongest windstorm of the field campaign T-REX occurred. The observed features of this event resemble the classical notion of a rotor. Altogether, the Doppler lidar observations of both downslope flow events reveal a complex, turbulent flow that is highly transient, intermittent, 3D, and interacts with a significant along-valley flow.
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Allen, C. B. "Multigrid multiblock hovering rotor solutions." Aeronautical Journal 108, no. 1083 (2004): 255–61. http://dx.doi.org/10.1017/s000192400000511x.

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AbstractThe effect of multigrid acceleration implemented within an upwind-biased Euler method for hovering rotor flows is presented. Previous work has considered multigrid convergence for structured single block rotor solutions. However, for forward flight simulation a multiblock approach is essential and, hence, the flow-solver has been extended to include multigrid acceleration within a multiblock solver. The requirement to capture the vortical wake development over several turns means a long numerical integration time is required for hovering rotors, and the solution (wake) away from the blade is significant. Hence, the solution evolution and convergence is different to a fixed wing case where convergence depends primarily on propagating errors away from the surface as quickly as possible, and multigrid acceleration is shown here to be less effective for hovering rotor flows. Previous single block simulations demonstrated that a simple multigridV-cycle was the most effective, smoothing in the decreasing mesh density direction only, with a relaxed trilinear prolongation operator. This is also shown to be the case for multiblock simulations. Results are presented for multigrid computations with 2, 3, and 4, mesh levels, and a CPU reduction of approximately 80% is demonstrated for 4 mesh levels.
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Dissertations / Theses on the topic "Rotor flows"

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Dehaeze, Florent. "Aeroelastic analysis of turbulent rotor flows." Thesis, University of Liverpool, 2012. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.570227.

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This thesis is devoted to the study of rotor flows. A literature survey suggested that possible improvements can be achieved via better simulation of turbulence and prediction of the elastic blade de- formation. While the limits of the currently used URANS turbulence models have been shown, accurate predictions can only be achieved if the blade elasticity is taken account due to the large deformations a rotor blade can undergo in flight. An aeroelastic coupling strategy consists in three steps: computing the flow field, computing the structural deformation and transferring data between the CFD and CSD solvers. The transfer method also needs to deal with the different sizes for the structural and aerodynamic models. Most challenges come from the need to modify the CFD mesh following the blade deformation, and are linked to the higher refinement of the CFD grid. To tackle the problem, a new hybrid mesh deformation technique, adapted to rotor in-flight deformations was developed for the Helicopter Multi-Block solver of Liver- pool. Demonstration of the method was presented for multiple test cases: hovering HART-II rotors and forward flying ONERA 7A and HART-II rotors. The method proved quick at deforming the mesh and able to deal with large rotor deformations without downgrading the mesh quality. Another point of interest in this work was turbulence modelling. Aeroelastic calculations must capture the influence of the flow on the blade structure. Rotorcraft flows are complex, and due to the lim- its of the URANS models in predicting the frequency content in the flow, discrepancies in the structural forcing and the blade deformation might appear. Vibration levels might also see an improvement from a higher frequency content. The potential of DES models for rotorcraft flow was demonstrated using the stalled flow around a NACA002l wing as a test case. The frequency content obtained through DES was much wider and also allowed for better predictions of the mean flow field properties along with integrated loads. DES was applied to the HART-II rotor in order to assess the possible improvements coming from the use of DES. However, the difference between the URANS and the DES predictions of the flow field were limited, highlighting a grid or time step refinement need. A strong aeroelastic coupling strategy was also demonstrated, using the UH-60A rotor in high- speed forward flight. The key structural deformation was captured by the coupling strategy, and the dependency of the predictions to many flight and simulation parameters was highlighted.
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Berkman, Mert Enis. "An integrated Navier Stokes-full portential-free wake method for rotor flows." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12388.

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Lee, Betty. "Dynamic response of small turbine flowmeters in pulsating liquid flows." Thesis, Brunel University, 2002. http://bura.brunel.ac.uk/handle/2438/4971.

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The dynamic response of turbine flowmeters in low pressure gas flows (i. e. where the rotational inertia of the fluid is negligible) is well understood and methods for correcting meter signals for a lack of response are available. For liquid flows there has been a limited amount of experimental work on the response of meters to step changes but no reports have been found of the response of meters to sinusoidally pulsating flows. "Small" turbine meters are expected to behave differently from "large" meters for a number of reasons: a smaller meter would generally have: (1) a larger percentage of tip clearance leakage flow; (2) less fluid momentum between the meter blading; and, (3) less fluid friction forces on the effective surface area. In this research, arbitrarily, meters up to size 25 mm were defined as small; and within this study, meters of size 6 mm to 25 mm were investigated. The aim of the research was to investigate and to understand the response of small turbine meters to pulsating liquid flows and to provide methods for correction. Three approaches were used: (1) application of an existing theoretical model of turbine meter behaviour; (2) an experimental investigation of meter performance in pulsating flows; and (3) simulation of flow behaviour through one selected meter using CFD and extending the simulation to predict the rotor dynamics and, hence, the response of this meter to specified cases of pulsating flow. A theoretical model developed by Dijstelbergen (1966) assumes frictionless behaviour and that flow is perfectly guided by meter blading through the rotor and that fluid within the rotor envelope rotates as a "solid body". Results from this theoretical model applied for pulsating flows showed that there was likely to be positive error in predicted mean flow rate (over-registration) and negative error for predicted values of the amplitude of the pulsations (amplitude attenuation). This behaviour is due to the fundamental asymmetry between flows with increasing and decreasing angle of attack relative to the meter blades, throughout a pulsation cycle. This qualitative behaviour was confirmed by experimental work with meters up to size 25mm working with pulsation frequencies up to 300 Hz. For low frequency pulsations (below 10 Hz), the over-registration errors were within the limits of specified meter accuracy. At higher frequencies and larger pulsation amplitudes, the largest over-registration observed was 5.5 % and amplitude attenuation could be as large as 90 %. The dependence of these errors on both the flow pulsation amplitude and frequency were investigated. The theoretical model was also used as a basis for generating correction procedures, to be applied to both the mean flow and the pulsation amplitude measurements. The results from the CFD simulation showed qualitative good agreement with the experimental data. The same kind of meter error trends were observed and it was shown to provide a better correlation with the experimental trends than the theoretical model derived from Dijstelbergen. From the CFD simulation, the causes of over-registration and amplitude attenuation in turbine flowmetering were understood through the investigation of rotor dynamics coupled with fluid behaviour around meter blading within the pulsation cycle. The CFD results were used to evaluate fluid angular momentum flux and to review the validity of the assumption that fluid within the rotor "envelope" rotated as a solid body. For the case investigated, whilst the assumption that flow is perfectly guided is not inappropriate, the volume of fluid assumed to rotate as a "solid body" was found to be significantly less than the rotor envelope volume.
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Wang, Chun-Wei. "Prediction of turbine cascade flows with a quasi-three-dimensional rotor viscous code and the extension of the algebraic turbulence model." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/24012.

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Approved for public release; distribution is unlimited<br>A quasi- three-dimensional rotor viscous code is used to predict high subsonic flow through an annular cascade of turbine blades. The well known Baldwin- Lomax turbulence model is used in the program. An attempt was made to implement a new turbulence model, based on renormalization group theory in the program. This was done to improve the prediction of the boundary layer transition on the blade surfaces . and subsequent wake development. The comparison of these two turbulence models with experimental data are presented. Pressure, velocity ratio, flow angle distributions and downstream wake predictions were studied using results from RVCQ3D (Rotor Viscous Code Quasi -Three -Dimensional) code. The computed results showed good agreement with experiment when comparing the blade surface local static pressure to inlet total pressure ratio at the midspan position of the annular turbine cascade. The computational approach used to implement the turbulence model is also described.
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Arisi, Allan Nyairo. "Heat Transfer and Flow Characteristics on the Rotor Tip and Endwall Platform Regions in a Transonic Turbine Cascade." Diss., Virginia Tech, 2016. http://hdl.handle.net/10919/64501.

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This dissertation presents a detailed experimental and numerical analysis of the aerothermal characteristics of the turbine extremity regions i.e. the blade tip and endwall regions. The heat transfer and secondary flow characteristics were analyzed for different engine relevant configurations and exit Mach/Reynolds number conditions. The experiments were conducted in a linear blowdown cascade at transonic high turbulence conditions of Mexit ~ 0.85, 0.60 and 1.0, with an inlet turbulence intensity of 16% and 12% for the vane and blade cascade respectively. Transient infrared (IR) thermography technique and surface pressure measurement were used to map out the surface heat transfer coefficient and aerodynamic characteristics. The experiments were complemented with computational modeling using the commercial RANS equation solver ANSYS Fluent. The CFD results provided further insight into the local flow characteristics in order to elucidate the flow physics which govern the measured heat transfer characteristics. The results reveal that the highest heat transfer exists in regions with local flow reattachment and new-boundary layer formation. Conversely, the lowest heat transfer occurs in regions with boundary layer thickening and separation/lift-off flow. However, boundary layer separation results in additional secondary flow vortices, such as the squealer cavity vortices and endwall auxiliary vortex system, which significantly increase the stage aerodynamic losses. Furthermore, these vortices result in a low film-cooling effectiveness as was observed on a squealer tip cavity with purge flow. Finally, the importance of transonic experiments in analyzing the turbine section heat transfer and flow characteristics was underlined by the significant shock-boundary layer interactions that occur at high exit Mach number conditions.<br>Ph. D.
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Peres, Noele. "A 3D pseudospectral method for cylindrical coordinates. Application to the simulations of rotating cavity flows." Thesis, Aix-Marseille, 2012. http://www.theses.fr/2012AIXM4309/document.

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La simulation d'écoulements dans des cavités cylindriques en rotation présente une difficulté particulière en raison de l'apparition de singularités sur l'axe. Le présent travail propose une méthode collocative pseudospectrale suffisamment efficace et précise pour surmonter cette difficulté et résoudre les équations 3D de Navier-Stokes écrites en coordonnées cylindriques. Cette méthode a été développée dans le cadre des différentes études menées au laboratoire M2P2, utilisant une méthode collocative de type Chebychev dans les directions radiale et axiale et Fourier-Galerkin dans la direction azimutale [thêta]. Pour éviter de prescrire des conditions sur l'axe, une nouvelle approche a été développée. Le domaine de calcul est défini par (r,[thêta],z)&#8712;[-1,1]×[0,2π]×[-1,1] avec un nombre N pair de points de collocation dans la direction radiale. Ainsi, r=0 n'est pas un point de collocation. La distribution de points de type Gauss-Lobatto selon r et z densifie le maillage seulement près des parois ce qui rend l'algorithme bien adapté pour simuler les écoulements dans des cavités cylindriques en rotation. Dans la direction azimutale, le chevauchement des points dû à la discrétisation est évitée par l'introduction d'un décalage égal à π/2K à [thêta]&gt;π dans la transformée de Fourier. La méthode conserve la convergence spectrale. Des comparaisons avec des résultats expérimentaux et numériques de la littérature montrent un très bon accord pour des écoulements induits par la rotation d'un disque dans des cavités cylindriques fermées<br>When simulating flows in cylindrical rotating cavities, a difficulty arises from the singularities appearing on the axis. In the same time, the flow field itself does not have any singularity on the axis and this singularity is only apparent. The present work proposes an efficient and accurate collocation pseudospectral method for solving the 3D Navier-Stokes equations using cylindrical coordinates. This method has been developed in the framework of different studies of rotor-stator flows, using Chebyshev collocation in the radial and axial directions and Fourier-Galerkin approximation in the azimuthal periodic direction [thêta]. To avoid the difficulty on the axis without prescribing any pole and parity conditions usually required, a new approach has been developed. The calculation domain is defined as (r,[thêta];,z)&#8712;[-1,1]×[0,2π]×[-1,1] using an even number N of collocation points in the radial direction. Thus, r=0 is not a collocation point. The method keeps the spectral convergence. The grid-point distribution densifies the mesh only near the boundaries that makes the algorithm well-suited to simulate rotating cavity flows where thin layers develop along the walls. In the azimuthal direction, the overlap in the discretization is avoided by introducing a shift equal to π/2K for [thêta]&gt;π in the Fourier transform. Comparisons with reliable experimental and numerical results of the literature show good quantitative agreements for flows driven by rotating discs in cylindrical cavities. Associated to a Spectral Vanishing Viscosity, the method provides very promising LES results of turbulent cavity flows with or without heat transfer
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Courtiade, Nicolas. "Experimental analysis of the unsteady flow and instabilities in a high-speed multistage compressor." Phd thesis, Ecole Centrale de Lyon, 2012. http://tel.archives-ouvertes.fr/tel-00838695.

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The present work is a result of collaboration between the LMFA (Laboratoire de Mécanique des Fluides et d'Acoustique, Ecole Centrale de Lyon - France), Snecma and the Cerfacs. It aims at studying the flow in the 3.5-stages high-speed axial compressor CREATE (Compresseur de Recherche pour l'Etude des effets Aérodynamique et TEchnologique - rotation speed: 11543 RPM, Rotor 1 tip speed: 313 m/s), designed and built by Snecma and investigated at LMFA on a 2-MW test rig. Steady measurements, as well as laser velocimetry, fast-response wall static and total pressure measurements have been used to experimentally investigate the flow. The analysis focuses on two main aspects: the study of the flow at stable operating points, with a special interest on the rotor-stator interactions, and the study of the instabilities arising in the machine at low mass flow rates.The description of the unsteady flow field at stable operating points is done through measurements of wall-static pressure, total pressure and velocity, but also total temperature, entropy and angle of the fluid. It is shown that the complexity and unsteadiness of the flow in a multistage compressor strongly increases in the rear part of the machine, because of the interactions between steady and rotating rows. Therefore, a modal analysis method developed at LMFA and based on the decomposition of Tyler and Sofrin is presented to analyze these interactions. It is first applied to the pressure measurements, in order to extract the contributions of each row. It shows that all the complex pressure interactions in CREATE can be reduced to three main types of interactions. The decomposition method is then applied to the entropy field extracted from URANS CFD calculations performed by the Cerfacs, in order to evaluate the impact of the interactions on the performance of the machine in term of production of losses.The last part of this work is devoted to the analysis of the instabilities arising in CREATE at low mass flows. It shows that rotating pressure waves appear at stable operating points, and increase in amplitude when going towards the surge line, until reaching a critical size provoking the onset a full span stall cell bringing the machine to surge within a few rotor revolutions. The study of these pressure waves, and the understanding of their true nature is achieved through the experimental results and the use of some analytical models. A precise description of the surge transient through wall-static pressure measurements above the rotors is also provided, as well as a description of a complete surge cycle. An anti-surge control system based on the detection of the amplitude of the pressure waves is finally proposed.
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Gougeon, Pierre. "Interactions aérodynamiques entre une turbine haute pression et le premier distributeur basse pression." Thesis, Ecully, Ecole centrale de Lyon, 2014. http://www.theses.fr/2014ECDL0026/document.

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L’amélioration des performances des turboréacteurs actuels est un enjeu crucial dans un contexte de contraintes économiques et environnementales fortes. Au sein du turboréacteur, le canal inter-turbines, localisé à l’interface entre la turbine Haute Pression (HP) et le premier distributeur Basse Pression (BP), est le siège d’écoulements très complexes. Ainsi, les structures aérodynamiques issues de la turbine HP (sillages, tourbillons et ondes de choc) interagissent fortement entre elles et impactent l’écoulement du distributeur BP, engendrant ainsi des pertes de rendement de l’ensemble de la configuration. Ce travail de thèse s’attache à étudier les phénomènes d’interactions aérodynamiques entre une turbine HP et le premier distributeur BP et à analyser les mécanismes à l’origine des pertes aérodynamiques dans le distributeur BP. Une campagne expérimentale antérieure, réalisée sur un banc d’essai comprenant une turbine HP couplée à un distributeur BP, avait permis de recueillir des mesures de l’écoulement dans des plans situés dans le canal inter-turbines et à l’aval du distributeur BP. En lien avec ces résultats expérimentaux, les simulations numériques menées dans cette étude avec le logiciel elsA s’attachent à restituer précisément la nature tridimensionnelle, instationnaire et turbulente de l’écoulement au sein de cette même configuration. Ces travaux se développent alors en trois étapes principales. Dans un premier temps, une étude stationnaire avec traitement plan de mélange permet de comprendre et quantifier les aspects généraux de l’écoulement. Une évaluation de l’effet de la modélisation turbulente RANS (Reynolds-Averaged Navier-Stokes) et du schéma numérique spatial sur les structures aérodynamiques présentes dans la configuration est réalisée. Dans un deuxième temps, une modélisation turbulente avancée de type ZDES (Zonal Detached-Eddy Simulation) est employée pour la résolution de l’écoulement dans le distributeur BP. Les structures aérodynamiques instationnaires issues de la roue HP amont sont modélisées par une condition limite à l’entrée du domaine de calcul. L’approche ZDES est comparée à une approche Unsteady RANS (URANS) sur la même configuration. La formation et la dissipation des sillages et des tourbillons est significativement différente entre les deux modélisations, ce qui impacte de manière importante la génération des pertes aérodynamiques. Enfin, des simulations URANS de plusieurs configurations permettent de mieux comprendre les effets d’interaction entre les différentes rangées d’aubes. Ainsi, les approches instationnaires chorochroniques prenant en compte un seul rotor et un seul stator évaluent des effets instationnaires importants dans le canal inter-turbines. Ces approches conduisent à la mise en oeuvre d’un calcul sur une configuration multipassages-chorochronique prenant en compte les deux stators et le rotor afin de modéliser complètement les interactions déterministes existantes. Afin de quantifier celles-ci avec précision, une décomposition modale du champ instationnaire est mise en place. Les niveaux d’interactions liées aux différentes roues sont alors quantifiés et l’impact sur les pertes aérodynamiques est évalué<br>Improving the performance of current aeronautical turbines is an important issue in a context of severe economical and environmental constraints. In a turbofan, the inter-turbine channel which is located between the High-Pressure (HP) turbine and the first Low Pressure (LP) vane is characterized by a complex flow. Therefore aerodynamic structures coming from the HP turbine (wakes, vortices and showkwaves) strongly interact between each other and affect the LP vane flow field. This generates efficiency losses of the overall configuration. This PhD thesis aims at studying the aerodynamic phenomena between a HP turbine and the first LP vane and at analyzing the mechanisms creating aerodynamic losses. A previous experimental campaign, which was carried out on a facility including a HP turbine coupled to a LP vane, enabled to gather flow field measurements in planes located in the inter-turbine channel and downstream of the LP vane. In comparison with these experimental data, the numerical simulations done with elsA software intend to reproduce accurately the 3D, unsteady and turbulent nature of the flow within this configuration. The work can be divided into three mains steps. As a first step, steady simulations with a sliding mesh treatment enable to understand the general aspects of the flow. An assessment of the effects of RANS (Reynolds-Averaged Navier-Stokes) turbulent predictions and of spatial numerical schemes on the aerodynamic structures present in the configuration is carried out. As a second step, the advanced turbulence approach ZDES (Zonal Detached-Eddy Simulation) is considered for the LP vane flow prediction. The unsteady aerodynamic structures coming from the upstream HP rotor are set as an inlet boundary condition of the computational domain. The ZDES approach is compared to a URANS (Unsteady RANS) approach on the same computational domain. The generation and dissipation of the wakes and vortices are significantly different on the two simulations, and thus impact the creation of aerodynamic losses. Finally, URANS simulations enable to better understand the interaction effects between the different blade rows. First, the unsteady phase-lagged approaches that take into account a single rotor and stator assess the important unsteady effects in the inter-turbine channel. They finally lead to the implementation of a multipassages phase-lagged computation that takes into account the two stators and the rotor in order to model all the existing determinist interactions. In order to quantify them accurately, a modal decomposition of the unsteady flow field is set up. The interaction levels linked to the different blade rows are therefore quantified and the impact of the aerodynamic losses is evaluated
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Vasilescu, Roxana. "Helicopter blade tip vortex modifications in hover using piezoelectrically modulated blowing." Diss., Available online, Georgia Institute of Technology, 2004:, 2004. http://etd.gatech.edu/theses/available/etd-11192004-165246/unrestricted/vasilescu%5Froxana%5F200412%5Fphd.pdf.

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Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2005.<br>Dancila, Stefan, Committee Chair ; Sankar, Lakshmi, Committee Member ; Ruzzene, Massimo, Committee Member ; Smith, Marilyn, Committee Member ; Yu, Yung, Committee Member. Vita. Includes bibliographical references.
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Beck, Stephen. "Full-Scale Tilt Rotor Download Reduction." Thesis, The University of Arizona, 2013. http://hdl.handle.net/10150/293744.

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A large-scale model of a tiltrotor wing and flap was built and tested to determine how the size and spacing of fluidic actuators for active flow control should be scaled up from laboratory size models to aircraft size. Flow control was provided by sweeping jet actuators mounted in the flap follower. Chordwise pressure data was collected through pressure taps located along the model centerline. The maximum flap deflection to which the flow could be attached with actuation was compared to previous experiments on a 10% 3D model. An ideal actuator spacing was found and the momentum coefficient was comparable between the various sized models. These results were used in the design of an industrial wind tunnel-scale model of a wing built for cruise and tiltrotor-like download testing. These tests have shown that actuators located in the flap follower are effective in both the hover and cruise phases of flight.
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Books on the topic "Rotor flows"

1

N, Duque Earl P., and United States. National Aeronautics and Space Administration., eds. Helicopter rotor blade computation in unsteady flows using moving overset grids. American Institute of Aeronautics and Astronautics, 1996.

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United States. National Aeronautics and Space Administration., ed. Viscous analysis of three-dimensional rotor flows using a multigrid method. National Aeronautics and Space Administration, 1993.

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United States. National Aeronautics and Space Administration., ed. Viscous analysis of three-dimensional rotor flows using a multigrid method. National Aeronautics and Space Administration, 1993.

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Boretti, A. A. Two-dimensional Euler and Navier Stokes time accurate simulations of fan rotor flows. NASA Lewis Research Center, Institute for Computational Mechanics in Propulsion, 1990.

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Boretti, A. A. Two-dimensional Euler and Navier Stokes time accurate simulations of fan rotor flows. NASA Lewis Research Center, Institute for Computational Mechanics in Propulsion, 1990.

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United States. National Aeronautics and Space Administration., ed. A k-[omega] turbulence model for quasi-three-dimensional turbomacinery flows. National Aeronautics and Space Administration, 1995.

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United States. National Aeronautics and Space Administration., ed. A k-[omega] turbulence model for quasi-three-dimensional turbomacinery flows. National Aeronautics and Space Administration, 1995.

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United States. National Aeronautics and Space Administration., ed. A k-[omega] turbulence model for quasi-three-dimensional turbomacinery flows. National Aeronautics and Space Administration, 1995.

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United States. National Aeronautics and Space Administration., ed. A k-[omega] turbulence model for quasi-three-dimensional turbomacinery flows. National Aeronautics and Space Administration, 1995.

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Yamamoto, Atsumasa. Three-dimensional flows and loss generation mechanisms in a linear turbine rotor cascade at various incidence conditions. National Aerospace Laboratory, 1988.

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Book chapters on the topic "Rotor flows"

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Luczak, Marcin M. "Uncertainty Quantification of the Main Rotor Blades Measurements." In Recent Progress in Flow Control for Practical Flows. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-50568-8_22.

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Berezin, Ihor. "Modal Analysis of PZL-W-3/W-3A Sokol Main Rotor." In Recent Progress in Flow Control for Practical Flows. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-50568-8_20.

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Tejero, Fernando, Piotr Doerffer, Paweł Flaszyński, and Oskar Szulc. "Implementation of Rod Vortex Generators on Helicopter Rotor Blades in Hover and Forward Flight Conditions." In Recent Progress in Flow Control for Practical Flows. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-50568-8_9.

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Serre, Eric, Patrick Bontoux, and Brian Launder. "Studies of Transitional and Turbulent Flows in Rotor-Stator Cavity Using High-Performance Computations." In Direct and Large-Eddy Simulation V. Springer Netherlands, 2004. http://dx.doi.org/10.1007/978-1-4020-2313-2_22.

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Shishkin, A., and C. Wagner. "Large Eddy Simulation of Turbulent Flows around a Rotor Blade Segment Using a Spectral Element Method." In Springer Proceedings in Physics. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-02225-8_28.

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Shishkin, A., and C. Wagner. "Large Eddy Simulation of Turbulent Flows Around a Rotor Blade Segment Using a Spectral Element Method." In Direct and Large-Eddy Simulation VII. Springer Netherlands, 2010. http://dx.doi.org/10.1007/978-90-481-3652-0_79.

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Pastrikakis, Vasileios, René Steijl, and George Barakos. "Performance Enhancement of Rotors in Hover Using Fixed Gurney Flaps." In Recent Progress in Flow Control for Practical Flows. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-50568-8_3.

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Dimarogonas, Andrew D., Stefanos A. Paipetis, and Thomas G. Chondros. "Flow-Induced Vibration of Rotating Shafts." In Analytical Methods in Rotor Dynamics. Springer Netherlands, 2013. http://dx.doi.org/10.1007/978-94-007-5905-3_4.

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Dimarogonas, Andrew D., Stefanos A. Paipetis, and Thomas G. Chondros. "Heat-Flow-Induced Vibration of Rotating Shafts: The Newkirk Effect." In Analytical Methods in Rotor Dynamics. Springer Netherlands, 2013. http://dx.doi.org/10.1007/978-94-007-5905-3_5.

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Fujisawa, Nobuyuki. "Visualization of Flow Phenomena in and Around a Savonius Rotor." In Flow Visualization VI. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84824-7_49.

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Conference papers on the topic "Rotor flows"

1

Schmitz, Sven, Nicholas Jaffa, David Reich, et al. "Flow Diagnostics of Scaled-Model Coaxial Rotor Hub Flows." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1130.

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Rotor hub parasite drag remains one of the challenges in further improving the forward-flight capabilities of coaxial rotorcraft. Comprehensive datasets on notional coaxial hub configurations are rare, and more so at Reynolds numbers sufficiently high to preserve dominating flow structures downstream into the wake where they interact with the rotorcraft empennage and tail. The present investigation was designed specifically to improve the understanding of interactional aerodynamics effects and wake flow physics of counter-rotating coaxial rotor hubs. A unique dataset is presented on a rotor hub design equipped with the DBLN 526 airfoil at a diameter-based Reynolds number of 1.13x106, corresponding to approximately quarter-scale Reynolds conditions of a coaxial compound helicopter at 200 knots. The experiments measured the time-averaged and time-varying drag on the hub configuration, with focus on a cruise advance ratio of 0.25 and a high-speed condition at 0.60. In addition to measuring hub drag and its harmonic content, a unique aspect of the experiment was the use of multiple non-invasive flow-diagnostics techniques for the particular hub configuration, advance ratios, and Reynolds number. Specifically, stereoscopic particle-image velocimetry (SPIV) measured the three velocity components at two downstream locations in the hub wake, thus providing insight into and visualizing the development of the wake. In addition, a limited laser-doppler velocimetry (LDV) and a tomographic PIV (Tomo-PIV) data campaign were conducted that confirm the earlier SPIV measurements. A subset of all measurements is presented. Some new insight into the flow physics was gained, one example being the dependence of higher-harmonic per-rev flow structures in the wake on hub advance ratio.
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Coder, James, Philip Cross, and Marilyn Smith. "Turbulence Modeling Strategies for Rotor Hub Flows." In Vertical Flight Society 73rd Annual Forum & Technology Display. The Vertical Flight Society, 2017. http://dx.doi.org/10.4050/f-0073-2017-11994.

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The influence of turbulence modeling strategy for computational fluid dynamics simulations of rotor hub flows is assessed. Two specific modeling strategies are discussed and applied to a representative rotor hub geometry that was the focus of the First Rotor Hub Flow Prediction Workshop and for which high-Reynolds number force data and wake measurements are available from a water-tunnel experiment. Simulations with both turbulence models were performed on the same structured, overset grid system using the same flow solver. Identical solution strategies were employed, including time accuracy, spatial discretization, and implicit algorithm. Several aspects of the solutions are compared, including mass-flow rate through the domain, unsteady drag characteristics, and unsteady wake characteristics.
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Yoon, Steven, Henry C. Lee, and Thomas H. Pulliam. "Computational Analysis of Multi-Rotor Flows." In 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-0812.

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Yoon, Steven, William M. Chan, and Thomas H. Pulliam. "Computations of Torque-Balanced Coaxial Rotor Flows." In 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0052.

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STEINHOFF, JOHN, and K. RAMACHANDRAN. "Free wake analysis of compressible rotor flows." In 25th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-542.

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Dawson, Michael G., and Nicholas R. Atkins. "The Effect of Rotor Leakage Flows on Hot Gas Ingestion." In ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2024. http://dx.doi.org/10.1115/gt2024-129257.

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Abstract The geometry of a turbine rotor disc has spaces through which parasitic leakage flows can leave the upstream disk cavity, affecting the purge flow required to maintain acceptable cavity temperatures. This paper presents a study of the effects of leakage flows through gas turbine rotors on hot gas ingestion into rotor-stator cavities. By modulating the area of rotor leakage paths, it is shown experimentally and numerically that, as expected, rotor leakage increases the purge flow required to maintain acceptable average cavity temperatures. However, the study also shows that through disc leakage exacerbates the effects of non-uniform ingestion, increasing the magnitude of local peaks in surface temperature for a given cavity average value. An empirical low-order model is proposed for the flow in the rotorstator cavity which captures the sensitivity of seal effectiveness to purge flow when leakage is present.
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Yoon, Seokkwan, Neal Chaderjian, Thomas H. Pulliam, and Terry Holst. "Effect of Turbulence Modeling on Hovering Rotor Flows." In 45th AIAA Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-2766.

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STEINHOFF, JOHN, WENREN YONGHU, THOMAS MERSCH, and HEINRICH SENGE. "Computational vorticity capturing - Application to helicopter rotor flows." In 30th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-56.

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Garcia, Antonio, Simone Colonia, and George N. Barakos. "Accurate predictions of hovering rotor flows using CFD." In 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1666.

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RAMACHANDRAN, K., J. STEINHOFF, and F. CARADONNA. "The free-wake computation of rotor-body flows." In 21st Fluid Dynamics, Plasma Dynamics and Lasers Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1540.

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Reports on the topic "Rotor flows"

1

Hawley. PR-015-11707-R01 Test Diagnostic Methods for Turbine Gas Meters. Pipeline Research Council International, Inc. (PRCI), 2013. http://dx.doi.org/10.55274/r0010671.

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Similar to most metering technologies, turbine meters are known to be affected by abnormal flow or abnormal mechanical conditions which can cause bias in flow measurement. These types of flow conditions include blockage at the flow meter or straightening vanes, grime or liquid contamination on the internal meter components, damage to the internal meter components, and pulsation in the flow. With the introduction of ultrasonic and Coriolis meters for gas applications, the natural gas industry has embraced the concept of meters with embedded diagnostic capabilities. These capabilities allow the detection of potential problems with the flow behavior or meter condition that may lead to measurement error. Diagnostic measurements also exist for turbine meters. Some turbine meter manufacturers provide techniques for diagnosing proper meter performance through approaches that include unique design attributes (e.g., dual-rotors) or by monitoring the characteristics (shape, timing, etc.) of the pulses produced as blades pass a sensor. Various analog and digital signal analysis methods exist to interpret the output pulse characteristics to determine meter condition attributes such as bent blades and bearing wear. The objective of this research was to assess, through flow testing, the ability of various diagnostic methods to detect abnormal flow and abnormal mechanical conditions for both single and dual-rotor turbine meters. A secondary objective was to determine the amount of flow measurement error that could be present for the various flow conditions that were tested. The approach was to test three different diagnostic methods on a single-rotor and dual-rotor turbine meter at the Metering Research Facility at Southwest Research Institute. The selected diagnostic methods were the Smith MeterTM AccuLERT II from FMC Technologies, TurbinScope from Elster-Instromet, and The Turbo Corrector from Mercury Instruments. Tests were performed under controlled conditions and were designed to determine the ability of the selected diagnostics to detect various levels of flow meter or tube bundle blockage, grime buildup on the rotor or rotor bearings, damage to the rotor, or flow pulsations.
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Dorney, Daniel J., Roger L. Davis, and David E. Edwards. Investigation of Hot Streak Migration and Film Cooling Effects on Heat Transfer in Rotor/Stator Interacting Flows. Report 1. Defense Technical Information Center, 1992. http://dx.doi.org/10.21236/ada250688.

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Komerath, Narayanan M., Vrishank Raghav, and James DiOttavio. Diagnostics of Flow Suppression on Rotor Blades: Final Report. Defense Technical Information Center, 2009. http://dx.doi.org/10.21236/ada509447.

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Mittal, Rajat. Large-Eddy Simulation of the Tip-Flow of a Rotor in Hover. Defense Technical Information Center, 2005. http://dx.doi.org/10.21236/ada440555.

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Zanker. PR-343-10604-R01 Auto-Adjust and Auto-Checking Capabilities of Dual Rotor Turbine Meters. Pipeline Research Council International, Inc. (PRCI), 2011. http://dx.doi.org/10.55274/r0010746.

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The goals of this project were twofold: (1) to test various piping configurations that are typically installed upstream of the AGA-9 recommended default meter run to determine if the configurations can cause significant installation bias, and (2) to determine if any of the tested configurations cause sufficiently little bias to become acceptable design practice. The approach was to use three commercially-available ultrasonic flow meters to monitor changes in flow measurement accuracy and variations in the velocity profiles from common piping configurations typically installed upstream of the AGA-9 recommended default meter run. The tests were performed under controlled conditions in the SwRI Metering Research Facility (MRF) High Pressure Loop (HPL) and were designed to compare a baseline unidirectional AGA-9 recommended default installation, without upstream piping disturbances, to common piping configurations with piping disturbances upstream of the baseline run.
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Shiu, Henry, and Cornelis P. van Dam. Active Flow Control on Bidirectional Rotors for Tidal MHK Applications. Office of Scientific and Technical Information (OSTI), 2013. http://dx.doi.org/10.2172/1090896.

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Simpson, Roger L. The Near-Wall Behavior of Unsteady Vortical Flow Around the Tip of an Axial Pump Rotor Blade. Defense Technical Information Center, 2003. http://dx.doi.org/10.21236/ada421059.

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