Relevant bibliographies by topics / Propeler turbine

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Propeler turbine'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Propeler turbine"

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Wahyudi, B., S. Sudarmadji, S. Sarjiyana, and M. Maskuri. "Web innovation in horizontal wind pipe turbine propeler." IOP Conference Series: Materials Science and Engineering 1073, no. 1 (February 1, 2021): 012080. http://dx.doi.org/10.1088/1757-899x/1073/1/012080.

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Manness, Jessica, and Jay Doering. "An improved model for predicting the efficiency of hydraulic propeller turbines." Canadian Journal of Civil Engineering 32, no. 5 (October 1, 2005): 789–95. http://dx.doi.org/10.1139/l05-029.

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Field performance testing of hydraulic turbines is undertaken to define the head-power-discharge relationship that identifies the peak operating point of the turbine. This relationship is essential for the efficient operation of a hydraulic turbine. Unfortunately, in some cases it is not feasible to field test turbines because of time, budgetary, or other constraints. Gordon (2001) proposed a method of predicting and (or) simulating the performance curve for several types of turbines. However, a limited data set was available for the development of his model for certain types of turbines. Moreover, his model did not include a precise method of developing performance curves for rerunnered turbines. Manitoba Hydro operates a large network of hydroelectric turbines, which are subject to periodic field performance testing. This provided a large data set with which to refine the model proposed by Gordon (2001). Furthermore, since these data include rerunnered units, this provides an opportunity to refine the effects of rerunnering. Analysis shows that the accuracy of the refined model is within 2% of the performance test results for an "old" turbine, while for a newer turbine or a rerunnered turbine the error is within 1%. For both an old turbine and a rerunnered turbine, this indicates an accuracy improvement of 3% over the original method proposed by Gordon (2001).Key words: hydraulic turbine, efficiency, simulation modeling
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Xu, Yiyi, Pengfei Liu, Irene Penesis, and Guanghua He. "A panel method for both marine propulsion and renewable energy." Journal of Naval Architecture and Marine Engineering 16, no. 2 (December 19, 2019): 61–76. http://dx.doi.org/10.3329/jname.v16i2.35984.

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A computational hydrodynamics method was formulated and implemented as a tool from screw propeller propulsion to renewable energy performance prediction, design and optimization of horizontal axis turbines. As an example for tidal energy generation, a comparative analysis between screw propellers and horizontal axis turbines was presented, in terms of geometry and motion parameters, inflow velocity analysis and the implementation methodologies. Comparison and analysis are given for a marine propeller model and a horizontal axis turbine model that have experimental measurements available in literature. Analysis and comparison are presented in terms of thrust coefficients, shaft torque/power coefficients, blade surface pressure distributions, and downstream velocity profiles. The effect of number of blades from 2 to 5, of a tidal turbine on hydrodynamic efficiency is also obtained and presented. The key implementation techniques and methodologies are provided in detail for this panel method as a prediction tool for horizontal axis turbines. While the method has been proven to be accurate and robust for many propellers tested in the past, this numerical tool was also validated and presented for both tidal and wind turbines.
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Kuwana, Anna, Xue Yan Bai, Dan Yao, and Haruo Kobayashi. "Numerical Simulation for the Starting Characteristics of a Wind Turbine." Advanced Engineering Forum 38 (November 2020): 215–21. http://dx.doi.org/10.4028/www.scientific.net/aef.38.215.

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There are many types of wind turbine. Large propeller-type wind turbines are used mainly for large wind farms and offshore wind power generation. Small vertical-axis wind turbines (VAWTs) are often used in distributed energy systems. In previous studies on wind turbines, the basic characteristics such as torque coefficient have often been obtained during rotation, with the turbine rotating at a constant speed. Such studies are necessary for the proper design of wind turbines. However, it is also necessary to conduct research under conditions in which the wind direction and wind speed change over time. Numerical simulation of the starting characteristics is carried out in this study. Based on the flow field around the wind turbine, the force required to rotate the turbine is calculated. The force used to stop the turbine is modeled based on friction in relation to the bearing. Equations for the motion of the turbine are solved by their use as external force. Wind turbine operation from the stationary state to the start of rotation is simulated. Five parameters, namely, blade length, wind turbine radius, overlap, gap, and blade thickness, are changed and the optimum shape is obtained. The simulation results tend to qualitatively agree with the experimental results for steadily rotating wind turbines in terms of two aspects: (1) the optimal shape has an 20% overlap of the turbine radius, and (2) the larger the gap, the lower the efficiency.
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Pribadyo, Pribadyo, Hadiyanto H, and Jamari J. "Simulasi Performa Turbin Propeller Dengan Sudut Pitch Yang Divariasikan." Jurnal Mekanova: Mekanikal, Inovasi dan Teknologi 6, no. 1 (June 11, 2020): 54. http://dx.doi.org/10.35308/jmkn.v6i1.2257.

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Propeller turbine performance can be improved by changing the turbine design parameters. One method that was developed is to vary the blade angle on the runner's blades. Analysis of the influence of blade angle on propeller turbine performance is done through numerical simulations based on computational fluid dynamics. The simulation is done with variations of propeller turbine blade angles of 180, 230, and 280 at flow rates of 0.08 m/s to 0.5 m/s. Simulation results show turbines with 250 blade angles have the best performance compared to turbine blade angles of 230 and 280. While the turbine blade angles of 230 tend to have higher performance compared to angles of 280 even though both have peak values for the corresponding power coefficient. Keywords—Propeller turbine, runner blade, pitch angle, CFD simulation
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Gorban’, Alexander N., Alexander M. Gorlov, and Valentin M. Silantyev. "Limits of the Turbine Efficiency for Free Fluid Flow." Journal of Energy Resources Technology 123, no. 4 (August 14, 2001): 311–17. http://dx.doi.org/10.1115/1.1414137.

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An accurate estimate of the theoretical power limit of turbines in free fluid flows is important because of growing interest in the development of wind power and zero-head water power resources. The latter includes the huge kinetic energy of ocean currents, tidal streams, and rivers without dams. Knowledge of turbine efficiency limits helps to optimize design of hydro and wind power farms. An explicitly solvable new mathematical model for estimating the maximum efficiency of turbines in a free (nonducted) fluid is presented. This result can be used for hydropower turbines where construction of dams is impossible (in oceans) or undesirable (in rivers), as well as for wind power farms. The model deals with a finite two-dimensional, partially penetrable plate in an incompressible fluid. It is nearly ideal for two-dimensional propellers and less suitable for three-dimensional cross-flow Darrieus and helical turbines. The most interesting finding of our analysis is that the maximum efficiency of the plane propeller is about 30 percent for free fluids. This is in a sharp contrast to the 60 percent given by the Betz limit, commonly used now for decades. It is shown that the Betz overestimate results from neglecting the curvature of the fluid streams. We also show that the three-dimensional helical turbine is more efficient than the two-dimensional propeller, at least in water applications. Moreover, well-documented tests have shown that the helical turbine has an efficiency of 35 percent, making it preferable for use in free water currents.
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Adhikari, Pradhumna, Umesh Budhathoki, Shiva Raj Timilsina, Saurav Manandhar, and Tri Ratna Bajracharya. "A Study on Developing Pico Propeller Turbine for Low Head Micro Hydropower Plants in Nepal." Journal of the Institute of Engineering 9, no. 1 (June 29, 2014): 36–53. http://dx.doi.org/10.3126/jie.v9i1.10669.

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Most of the turbines used in Nepal are medium or high head turbines. These types of turbines are efficient but limited for rivers and streams in the mountain and hilly region which have considerably high head. Low head turbines should be used in the plain region if energy is to be extracted from the water sources there. This helps in the rural electrification and decentralized units in community, reducing the cost of construction of national grid and also to its dependency, in already aggravated crisis situation. There are good turbine designs for medium to high heads but traditional designs for heads under about 5m (i.e. cross flow turbine and waterwheel) are slow running, requiring substantial speed increase to drive an AC generator. Propeller turbines have a higher running speed but the airfoil blades are normally too complicated for micro hydro installations. Therefore, the open volute propeller turbine with constant thickness blades was ventured as possible solution. Such type of propeller turbine is designed to operate at low inlet head and high suction head. This enables the exclusion of closed spiral casing. Also, the constant thickness blades enable the use of forging process instead of casting of complex airfoil blades. This leads to considerable reduction in manufacturing cost and complexity. A 1kW prototype was designed and scale down model of 185W was fabricated and tested. The runner consisted of five blades of 4mm thickness with camber and twist. The runaway speed of 1058 rpm was attained at design flow rate of 25 l/s. At full load the efficiency of model was found to be about 57%. Applying scaling effects the expected efficiency of the prototype was estimated to be about 60%. DOI: http://dx.doi.org/10.3126/jie.v9i1.10669 Journal of the Institute of Engineering, Vol. 9, No. 1, pp. 36–53
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Nurdin, Akhmad, Dwi Aries Himawanto, and Syamsul Hadi. "Study of the Effect of Bulb Ratio and Blade Angle on Propeller Turbine Performance in Horizontal Flow using Numerical Simulation." TEKNIK 41, no. 1 (May 18, 2020): 9–13. http://dx.doi.org/10.14710/teknik.v41i1.25328.

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This paper discusses numerical simulations of horizontal flow propeller turbines. Static bulbs located before the turbine can be used to increase water velocity and potentially increase the turbine's performance. The blade angle affects the gap between the blades, and this will also affect the performance of the turbine. Numerical simulations were conducted by using software Solid Works Flow Simulation 2016 and by using five blades in a static state. This study aimed to determine the effect of the bulb ratio and blade angle on the propeller turbine characteristics on horizontal flow. Bulb Ratio variations used in this study were 0, 0.4, 0.6, and 0.8, while the angle variations used were 20, 25, and 30 degrees. Each variation was tested at 0.02 m3/second. The results of this study indicated that the bulb ratio 0.6 with the 25-degree blade angle produces the highest torque
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Burghardt, Andrzej, Krzysztof Kurc, and Dariusz Szybicki. "Robotic Automation of the Turbo-Propeller Engine Blade Grinding Process." Applied Mechanics and Materials 817 (January 2016): 206–13. http://dx.doi.org/10.4028/www.scientific.net/amm.817.206.

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Robotic automation of industrial processes in terms of the adaptation of the robot path to changing external conditions has recently been one of the main subjects of research and implementation studies. The presented study involved trailing plane grinding the turbine blades. The suggested automated station comprises an IRB 140 robot handling the processed element, grinding tool and an IRB 1600 robot with a 3D scanning head installed. The presented robotic automation solutions may be used for finishing operations on blades constituting elements of aircraft engines, power generating turbines and wind turbines.
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Suryadi, Aris, Mochamad Faisal, Berayan Munthe, Mindit Eriyadi, and Junaidy Burhan. "APLIKASI TEKNOLOGI PLTMH TURBIN PROPELLER OPEN FLUME SEBAGAI PEMBANGKIT LISTRIK DESA." SPEKTA (Jurnal Pengabdian Kepada Masyarakat : Teknologi dan Aplikasi) 1, no. 2 (November 10, 2020): 39. http://dx.doi.org/10.12928/spekta.v1i2.2742.

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Berecek Village, located in Sukatani District, Purwakarta Regency, West Java Province, has a river that has not been used optimally. This community service aims to utilize the available water energy so that it can produce Micro Hydro power plants. The manufacture of a micro-hydro power plant starts from measuring water potential, designing turbines and generators, then observing the work system and estimating the electrical power that will be generated. From the survey results, it is known that the water discharge is 0.0059 m3 / s and has a fall height of 4 m. This data is used to select the type of turbine, reservoir selection, quick pipe, and generator design. The results of the manufacture of micro power plants obtained by designing using an open flume propeller turbine with a turbine rotation speed of 2063 rpm, this PLTMH is able to produce turbine power of 1346 watts with a water discharge of 45 liters / second so that the power obtained is 1076 watts.
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Dissertations / Theses on the topic "Propeler turbine"

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Duda, Petr. "Optimalizace polohy propelerové turbíny v kašně." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2014. http://www.nusl.cz/ntk/nusl-231499.

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The thesis contains basic information about propeler turbines. It deals with the correct location in the fountain so as to ensure the highest possible performance. Part of the work is devoted to the all-weather resulting blade to blade channels and their impact on the room is filled with diffuser.
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Skidmore, F. W., and n/a. "The influence of gas turbine combustor fluid mechanics on smoke emissions." Swinburne University of Technology, 1988. http://adt.lib.swin.edu.au./public/adt-VSWT20070420.131227.

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This thesis describes an experimental program covering the development of certain simple combustion chamber modifications to alleviate smoke emissions from the Allison T56 turboprop engines operated by the Royal Australian Air Force. The work includes a literature survey, smoke emission tests on two variants of the T56 engine, flow visualisation studies of the combustion system in a water tunnel and combustion rig tests of a standard combustor and four possible modifications. The rig tests showed that reductions in smoke emissions of 80% were possible by simple modifications that reduced the primary zone equivalence ratio and improved mixing in that zone.
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Faulkner, Simon A. "A simplified low head propeller turbine for micro hydroelectric power." Thesis, University of Canterbury. Engineering, 1991. http://hdl.handle.net/10092/6456.

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This thesis describes the development of a simplified propeller turbine unit to produce power in a low head micro hydroelectric power installation. To be appropriate for remote areas and developing countries, a micro hydro system needs to be simple in design. There are good turbine designs for medium to high heads but traditional designs for heads under about 10m, ie, the crossflow turbine and waterwheel, are slow running, requiring substantial speed increase to drive an AC generator. Propeller turbines have a higher running speed but are normally too complicated for micro hydro installations. In this thesis a suitable propeller turbine was developed. The effect of flat blades and optimum turbine blade and guide vane angles has been determined, as has the effect of various cones attached to the downstream end of the hub. The large hub diameter is an important compromise. A prototype turbine for installation on a New Zealand farm was developed from model tests. The turbine has a hub diameter to blade tip diameter ratio of 0.66 and 8 flat blades set at 30° to tangential (60° from axial). The best efficiency of the model turbine was 62%, with an efficiency of 57% at the best power point. Using scaling laws it is predicted that the prototype, with a blade tip diameter of 0.410m, will produce 6.0kW at 612 RPM from a head of 2.7m and a flow rate of 0.41m³/s. This gives 4.3kW output from the 50Hz 2-pole generator. This prediction is for no cone fitted on the downstream end of the hub, but model tests indicate that the power could be improved by about 5% with the addition of a straight sided cone on the hub.
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Demetriades, Georgios Manoli. "Integral propeller turbine-induction generator units for village hydroelectric schemes." Thesis, Nottingham Trent University, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.363325.

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Fuller, Adam Michael. "Increasing the specific speed of simple microhydro propeller turbines." Thesis, University of Canterbury. Mechanical Engineering, 2011. http://hdl.handle.net/10092/6680.

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The late University of Canterbury civil engineering lecturer Peter Giddens developed a range of simple microhydro turbines, with publications from as early as the 1980s. He considered that a range of simple but well-designed turbines which covered the gamut of possible small sites would be more useful than any single turbine. He started with radial inflow turbines, then set about extending their range of applicability by increasing specific speed. That extension was continued by the research in this thesis, which aimed to produce a design with a minimum efficiency of 70 % at a specific speed of at least 600 (rev/min, kW, m). Achieving those targets would differentiate it from existing microhydro designs. In order to reach those performance targets, the volute, runner, and draft tube were examined through experiment and computational fluid dynamics models to characterize past designs and test the validity of their embodied assumptions. A prototype with a design specific speed of 650 was built and fully characterized by dynamometer testing. Measurements of the outlet velocity distribution of two of Peter Giddens’s volutes confirmed that single tangential inlet volutes are not torque-free when certain geometric conditions are met; swirl increased through those volutes by 70 % or more depending on the design. A new overall turbine design was proposed, where axial flow enters the runner and swirling flows leaves it. This required the design of a novel volute. Through computational analysis, the effect of swirling flow entering the conical draft tube was shown to affect its pressure recovery: negatively for draft tubes with small angles, positively for larger angles. It was shown that the peak pressure recovery of an optimum draft tube was not likely to be improved upon by the use of swirl, and since there was uncertainty in the analysis, a conservative draft tube was specified for the prototype. A flat-bladed runner was designed for the prototype and computational modeling indicated its performance would be sensitive to small changes in flow angle. Despite that sensitivity — an intrinsic property of high specific speed runner velocity triangles — the computational model was shown to give good predictions of the runner flow characteristics, although not its effciency. Finally, a 1.2 kW prototype was built and achieved a peak net effciency of 64 % as defined by the American Society of Mechanical Engineers at a net head of 2.07 m, a flowrate of 94 L/s, and a runner shaft speed of 1670 rev/min, corresponding to a specific speed of 740. Maximum measured runner efficiency of 87 % also occurred at those conditions. Compared to existing designs, that performance extended the operational envelope of microhydro turbines considerably. A three-zone computational model of the entire prototype was assembled and trialled, but not validated. It is concluded that for efficient high specific speed turbines, volute swirl characteristics must be known with confidence, as the volute sets the conditions at the leading edge for peak runner efficiency. A simple but efficient runner may be made using flat blades, showing the potential for this geometry even when made by limited workshops. Adding a free-vortex tangential velocity distribution to the inlet flow of a stalled conical draft tube may increase its pressure recovery, although it is not likely to exceed the best performance obtainable with axial inlet flow. Therefore taking measures to reduce the peak fluid velocity entering the draft tube could be more beneficial to overall performance than seeking outright improvements in draft tube pressure recovery.
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Gagnon, Jean-Mathieu. "Contribution to the study of the 3D unsteady flow in a propeller turbine." Thesis, Université Laval, 2012. http://www.theses.ulaval.ca/2012/28126/28126.pdf.

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Portocarrero, Aguilar Carlos Enrique. "Diseño de una turbina propeller utilizando plásticos reciclados reforzados con madera recuperada." Bachelor's thesis, Pontificia Universidad Católica del Perú, 2012. http://tesis.pucp.edu.pe/repositorio/handle/123456789/1215.

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El tema del calentamiento global es un gran debate entre políticos, científicos, la industria y la sociedad en general. Se discute desde su existencia hasta su severidad, sus potenciales causas, así como sus efectos en los sistemas globales tales como el clima, la ecología y particularmente en la vida de las personas. En este contexto, es indiscutible que las emisiones de dióxido de carbono y otras que intensifican el efecto invernadero han aumentado dramáticamente, a la par de nuestro consumo energético. Para revertir esta situación, por un lado, es impostergable el desarrollo de tecnologías que permitan aprovechar fuentes de energía renovable como la fluvial o la marítima que, por cierto, son abundantes en el Perú y, por otro, la utilización de materiales reciclados se hace cada vez más exigente para contribuir con el cuidado del medio ambiente. Una aplicación que sintetiza ambas soluciones, es la fabricación de rodetes de turbinas con materiales reciclados de bajo peso para garantizar el aprovechamiento eficiente de la energía de los ríos y mares. El objetivo de este trabajo es el diseño de una turbina de corriente libre tipo propeller utilizando plásticos reciclados reforzados con madera recuperada. El diseño de la turbina propeller realizado en el presente trabajo comprende las siguientes etapas: En primer lugar, se identificaron los parámetros necesarios para el diseño. Luego de un análisis energético, se procedió a realizar el dimensionamiento inicial del rotor de la turbina y mediante un análisis mecánico se determina el diseño final de la geometría y los materiales de los álabes. A continuación se diseñan los demás componentes y accesorios de la turbina. Por último, se realizan los planos y costos de fabricación. Se ha diseñado una turbina tipo propeller de eje inclinado a 30° con el plano horizontal, 2m de diámetro y tres álabes con perfil NACA 4412 en su sección transversal; capaz de desarrollar una potencia máxima en el eje de 1,1 kW. Para el diseño de los álabes se ha considerado que éstos serán fabricados en dos etapas: inicialmente el núcleo de los álabes se obtendrá por moldeo de un material compuesto de matriz de polipropileno reciclado reforzado con partículas de madera capirona recuperada y, finalmente, recubiertas con dos capas de material compuesto de fibra de vidrio y resina poliéster; reduciendo considerablemente los costos y tiempos de fabricación en comparación a los álabes fabricados en su totalidad con este último material compuesto.
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Houde, Sébastien. "Analysis of the part-load and speed-no-load flow dynamics in a model propeller hydraulic turbine." Doctoral thesis, Université Laval, 2018. http://hdl.handle.net/20.500.11794/29823.

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Les turbines hydrauliques sont devenues un atout important pour la régulation de la puissance sur les réseaux électriques. Cependant, les scénarios de régulation de puissance exigent que les turbines fonctionnent loin de leurs points d'opération optimale, dans des régions où de grandes uctuations de pression peuvent affecter l'intégrité structurale de la turbine. Cette thèse présente des contributions a l'etude de l'hydrodynamique de l'écoulement dans une turbine helice modele fonctionnant dans des conditions de charge partielle et de vitesse-sans-charge. À charge partielle, les fluctuations de pression principales sont associées à un vortex cavitant. Des mesures provenant de Vélocimétrie par Imagerie de Particules (PIV) couplées à des techniques de fluorescence induite par laser et d'ombroscopie ont été utilisées pour reconstruire l'interface eau-vapeur et identier l'origine de fluctuations aectant la précision des mesures de PIV moyennées en phase. De plus, des capteurs de pression miniatures incorporés dans deux aubes de la roue ainsi que des jauges de deformation montées sur les aubes ont fourni des données pour quantier l'impact du vortex de charge partielle sur la turbine. Cette thèse présente également l'une des premieres etudes detaillees sur les conditions transitoires et sans charge dans une turbine modèle. Les capteurs de pression et de déformation sur les aubes ont ete utilisés pour identier les instabilités dominantes dans des conditions de vitesse sans charge et d'emballement. Des simulations basées sur la technologie Scale Adaptive Simulations (SAS) de la condition de vitesse-sans-charge ont été utilisés pour étudier un décrochage tournant dans la roue. Des simulations sans les aubes indiquent que le décrochage tournant est associé à une couche cisaillée provenant d'une recirculation autour du moyeu de la roue et d'une séparation de la couche limite sur le fond supérieur.
Hydraulic turbines have become an important asset to provide power regulation on electrical grids. However, power-regulation scenarios require turbines to operate far from their best eciency conditions, in regions where large pressure uctuations aect the turbine structural integrity. This is particularly acute for xed blade reaction turbines such as propeller units. This thesis presents contributions to the study of the hydrodynamics of the ow in a model propeller turbine operating in part-load and speed-no-load conditions. In part load, the main pressure uctuations are associated with the part-load vortex. Data from Particle Image Velocimetry (PIV), coupled to Laser Induced Fluorescence and shadowgraphy techniques, were used to reconstruct the water-vapour interface and to identify the origin of uctuations aecting the precision of the phase-averaged PIV measurements. Furthermore, miniature pressure transducers imbedded in two runner blades and strain gages at the blade roots provided data to quantify the impact of the part load vortex on the runner. This thesis also presents one of the rst detailed studies on transient and no-load conditions in a model hydro-turbine. Pressure and strain sensors were used to identify the dominant ow instabilities in speed-no-load and runaway conditions. Scale Adaptive Simulations (SAS) of the speed-no-load condition were used to study a rotating stall dominating the runner ow. Simulations without runner blades indicate that the rotating stall is associated with an unstable shear-layer originating from a recirculation around the runner hub and a boundary layer separation on the turbine head cover. Those results open the possibility of eventually developing mitigation techniques.
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Leng, Yujun. "Preliminary design tools in turbomachinery| Non-uniformly spaced blade rows, multistage interaction, unsteady radial waves, and propeller horizontal-axis turbine optimization." Thesis, Purdue University, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10149746.

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Turbomachinery flow fields are inherently unsteady and complex which makes the related CFD analyses computationally intensive. Physically based preliminary design tools are desirable for parametric studies early in the design stage, and to provide deep physical insight and a good starting point for the later CFD analyses. Four analytical/semi-analytical models are developed in this study: 1) a generalized flat plate cascade model for investigating the unsteady aerodynamics of a blade row with non-uniformly spaced blades; 2) a multistage interaction model for investigating rotor-stator interactions; 3) an analytical solution for quantifying the impeller wake convection and pressure wave propagating between a centrifugal compressor impeller and diffuser vane; and 4) a semi-analytical model based Lifting line theory for unified propeller and horizontal-axis turbine optimization. Each model has been thoroughly validated with existing models.

With these models, non-uniformly spaced blade rows and vane clocking are investigated in detail for their potential use as a passive control technique to reduce forced response, flutter and aeroacoustic problems in axial compressors. Parametric studies with different impeller blade numbers and back sweep angles are conducted to investigate their effect on impeller wake and pressure wave propagation. Results show that the scattered pressure waves with high circumferential wave numbers may be an important excitation source to the impeller as their amplitude grows much faster as they travel inwardly than the lower order primary pressure waves. Detailed analysis of Lifting line theory reveals the mathematical and physical equivalence of Lifting line models for propellers and horizontal-axis turbines. With a new implementation, the propeller optimization code can be used for horizontal-axis turbine optimization without any modification. The newly developed unified propeller and horizontal-axis turbine optimization code based on lifting line theory and interior point method has been shown to be a very versatile tool with the capability of hub modelling, working with non-uniform inflow and including extra user specified constraints.

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Fjällman, Johan. "Large Eddy Simulations of Complex Flows in IC-Engine's Exhaust Manifold and Turbine." Doctoral thesis, KTH, Strömningsfysik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-151399.

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The thesis deals with the flow in pipe bends and radial turbines geometries that are commonly found in an Internal Combustion Engine (ICE). The development phase of internal combustion engines relies more and more on simulations as an important complement to experiments. This is partly because of the reduction in development cost and the shortening of the development time. This is one of the reasons for the need of more accurate and predictive simulations. By using more complex computational methods the accuracy and predictive capabilities are increased. The disadvantage of using more sophisticated tools is that the computational time is increasing, making such tools less attractive for standard design purposes. Hence, one of the goals of the work has been to contribute to assess and improve the predictive capability of the simpler methods used by the industry. By comparing results from experiments, Reynolds Averaged Navier-Stokes (RANS) computations, and Large Eddy Simulations (LES) the accuracy of the different computational methods can be established. The advantages of using LES over RANS for the flows under consideration stems from the unsteadiness of the flow in the engine manifold. When such unsteadiness overlaps the natural turbulence the model lacks a rational foundation. The thesis considers the effect of the cyclic flow on the chosen numerical models. The LES calculations have proven to be able to predict the mean field and the fluctuations very well when compared to the experimental data. Also the effects of pulsatile exhaust flow on the performance of the turbine of a turbocharging system is assessed. Both steady and pulsating inlet conditions are considered for the turbine case, where the latter is a more realistic representation of the real flow situation inside the exhaust manifold and turbine. The results have been analysed using different methods: single point Fast Fourier Transforms (FFT), probe line means and statistics, area and volume based Proper Orthogonal Decomposition (POD) and Dynamic Mode Decomposition (DMD).
Denna avhandling behandlar flödet i rörkrökar och radiella turbiner som vanligtvis återfinns i en förbränningsmotor. Utvecklingsfasen av förbränningsmotorer bygger mer och mer på att simuleringar är ett viktigt komplement till experiment. Detta beror delvis på minskade utvecklingskostnader men även på kortare utevklningstider. Detta är en av anledningarna till att man behöver mer exakta och prediktiva simuleringsmetoder. Genom att använda mer komplexa beräkningsmetoder så kan både nogrannheten och prediktiviteten öka. Nackdelen med att använda mer sofistikerade metoder är att beräkningstiden ökar, vilket medför att sådana verktyg är mindre attraktiva för standardiserade design ändamål. Härav, ett av målen med projektet har varit att bidra med att bedöma och förbättra de enklare metodernas prediktionsförmåga som används utav industrin. Genom att jämföra resultat från experiment, Reynolds Averaged Navier-Stokes (RANS) och Large Eddy Simulations (LES) så kan nogrannheten hos de olika simuleringsmetoderna fastställas. Fördelarna med att använda LES istället för RANS när det gäller de undersökta flödena kommer ifrån det instationära flödet i grenröret. När denna instationäritet överlappar den naturligt förekommande turbulensen så saknar modellen en rationell grund. Denna avhandling behandlar effekten av de cykliska flöderna på de valda numeriska modellerna. LES beräkningarna har bevisats kunna förutsäga medelfältet och fluktuationerna väldigt väl när man jämför med experimentell data. Effekterna som den pulserande avgasströmning har på turboladdarens turbin prestanda har också kunnat fastställas. Både konstant och pulserande inlopps randvillkor har används för turbinfallet, där det senare är ett mer realistiskt representation av den riktiga strömningsbilden innuti avgasgrenröret och turbinen. Resultaten har analyserats på flera olika sätt: snabba Fourier transformer (FFT) i enskilda punkter, medelvärden och statistik på problinjer, area och volumsbaserade metoder så som Proper Orthogonal Decomposition (POD) samt Dynamic Mode Decomposition (DMD).

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Books on the topic "Propeler turbine"

1

Dicmas, John L. Vertical turbine, mixed flow, and propeller pumps. New York: McGraw-Hill, 1987.

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Whitlow, John B. NASA advanced turboprop research and concept validation program. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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Anderson, R. D. Advanced propfan engine technology (APET) definition study, single and counter-rotation gearbox/pitch change mechanism design. [Washington, DC: National Aeronautics and Space Administration, 1987.

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Patterson, James C. Evaluation of installed performance of a wing-tip-mounted pusher turboprop on a semispan wing. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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Patterson, James C. Evaluation of installed performance of a wing-tip-mounted pusher turboprop on a semispan wing. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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Levin, Alan D. Aerodynamic and propeller performance characteristics of a propfan-powered, semispan model. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

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Litt, John. A real-time simulator of a turbofan engine. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Advanced technology for aero gas turbine components. Neuilly sur Seine, France: AGARD, 1987.

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Plencner, Robert M. Plotting component maps in the Navy/NASA Engine Program (NNEP): A method and its usage. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Rosen, Robert. The Future challenge for aeropropulsion. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1992.

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Book chapters on the topic "Propeler turbine"

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Harvey, Adam. "11. Crossflow Turbines; Reaction Turbines; The Francis Turbine; The Propeller Turbine and Kaplan; Draught Tubes; Reverse Pumps." In Micro-Hydro Design Manual, 173–86. Rugby, Warwickshire, United Kingdom: Practical Action Publishing, 1993. http://dx.doi.org/10.3362/9781780445472.011.

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Urlaub, Alfred. "Propeller-Turbinen-Luftstrahltriebwerke." In Flugtriebwerke, 119–27. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-78386-9_5.

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Urlaub, Alfred. "Propeller-Turbinen-Luftstrahltriebwerke." In Flugtriebwerke, 119–27. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-97322-2_5.

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Chattot, J. J., and M. M. Hafez. "Wind Turbine and Propeller Aerodynamics—Analysis and Design." In Theoretical and Applied Aerodynamics, 327–72. Dordrecht: Springer Netherlands, 2015. http://dx.doi.org/10.1007/978-94-017-9825-9_10.

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Billonnet, Gilles. "Supersonic Stator-Rotor Interaction in a Turbine Stage." In Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, 309–29. New York, NY: Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_16.

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Léonard, F. "Two Kinds of Whirl on Fixed-Blade Propeller Type Turbine." In Hydraulic Machinery and Cavitation, 885–94. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-010-9385-9_90.

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Junginger, Bernd, and Stefan Riedelbauch. "Numerical Analysis of a Propeller Turbine Operated in Part Load Conditions." In High Performance Computing in Science and Engineering ' 17, 355–68. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-68394-2_21.

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Chang, Jiang, and Yan Peng. "Construction and Simulation of the Movable Propeller Turbine Neural Network Model." In Advances in Machine Learning and Cybernetics, 133–41. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/11739685_14.

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Gallus, H. E., C. A. Poensgen, and J. Zeschky. "Three-Dimensional Unsteady Flow in a Single Stage Axial-Flow Turbine and Compressor." In Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, 487–505. New York, NY: Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_24.

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Bölcs, A., A. Cargill, T. H. Fransson, A. Suddhoo, and K. Vogeler. "Time-Dependent Predictions and Analysis of Turbine Cascade Data in the Transonic Flow Region." In Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, 289–308. New York, NY: Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_15.

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Conference papers on the topic "Propeler turbine"

1

Ranjanagi, Sagar, Quamber H. Nagpurwala, and S. Subbaramu. "Numerical Studies on the Effect of Design Trim on Aerodynamic Performance of a Micro Propeller for MAV Application." In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3671.

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Of late, the aerospace industry has taken increasing interest in Micro Air Vehicles (MAV) powered by electric motor driven micro propellers. The endurance of the MAV largely depends upon the propulsive efficiency of its propeller. This has created a need for improved design of propellers through an in-depth understanding of the relevant aerodynamics. Design of micro propellers operating at low Reynolds numbers with sufficiently high propulsive efficiency is a challenging task. This paper deals with the parametric studies on a micro propeller for MAV application through numerical simulations. A propeller of known geometry was selected from the published literature. Geometrical model of the baseline propeller was prepared using CATIA V5 software and CFD analysis was carried out using ANSYS FLUENT 12.0 software. The baseline geometry of the micro propeller was modified by varying the spanwise position of maximum blade chord, maximum chord length, and pitch to diameter ratio to generate new design variants. The performances of these design variants were analysed through CFD simulations and compared in terms of variation of efficiency, torque coefficient and thrust coefficient against advance ratio. No significant change was observed in performance by changing the location of maximum blade chord. However, the required thrust of 1 N was achieved by increasing the chord length by 1.2 times the base line design at an efficiency of 64.2%. The propeller efficiency was further increased to 70.8% at an increased pitch to diameter ratio of 1.2 and at an advance ratio of 1.033.
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Schmidt, Marvin F. "Propeller Design Point Calculation Method for Comparing Turbofan/Propfan Engine Performance." In ASME 1985 Beijing International Gas Turbine Symposium and Exposition. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-igt-150.

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This paper presents a method to calculate the design point performance of both single rotation and dual contra-rotation propellers. Major propeller variables such as, power loading (shaft horsepower/prop diameter2), propeller efficiency (Prop Thrust × Acft Veloc/shaft horsepower), propeller tip speed and propeller adiabatic compression efficiency are accounted for and correlated. The resulting propeller performance is then combined with given shaft power producer (engine) performance to yield propfan engine performance. The performance trades between power loading, propeller efficiency, propeller tip speed and propeller adiabatic compression efficiency are presented. Resulting performance, with a given engine, are presented in the form of Figs 7 and 8 for both single and dual contra-rotation propellers. These engine performances can then be compared to advanced turbofan engines that utilize identical technology shaft power producer engines.
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Murugesan, Ramesh, and Vijayanandh Raja. "Acoustic Investigation on Unmanned Aerial Vehicle’s Rotor Using CFD-MRF Approach." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2430.

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Abstract Future developments have been indicated for further research and development in the Aeroacoustics of the components of Unmanned Aerial Vehicles (UAVs). In which the implementation of multi-rotor UAVs in the complex applications is quite high but it has the drawback of high drive-line noise levels, which is one of the prime radar detectability factors. As a result, an idea is emerged to design and test the quite UAV, in which the noise from propellers plays a major role. in order to the successful completion of the design study, a complete is conducted, in which the design parameters and various noise reduction methodologies in the rotating components have been noted and included in the final design. To minimize the noise signature issue in UAV, the idea finalized that to minimize the decibel of small Unmanned Aircraft System (UAS) propellers via leading-edge modifications. A computer-aided design of base propeller and three different versions propeller with leading-edge modifications are generated with the help of CATIA for Computational Fluid Dynamics (CFD) simulations. Comparative noise variation simulations between the existing and the propellers with modification are performed, in which dynamic conditions play a predominant to initiate the analysis and thereby the analyses are carried out with the help of ANSYS Workbench Fluent 16.2. Especially, to make an acceptable solution, the Moving Reference Frame (MRF) approach is used in order to capture the propeller rotation in an effective manner. Finally, a propeller with airfoil cut at the leading edge has induced the low noise.
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Farghaly, Mohamed B., Ahmed F. El-Sayed, and Galal B. Salem. "Numerical Simulation of the Aerodynamic Behavior of Propeller Blades at Subsonic Conditions." In ASME 2012 Gas Turbine India Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gtindia2012-9733.

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The Organization of the Petroleum Exporting Countries (OPEC) oil crisis of the mid 1970s led to a revival in interest in the propeller as a possible fuel-efficient propulsion for aircraft operating at subsonic cruise speeds. A propeller aerodynamics is complex and should be analyzed carefully to ensure maximum propellers efficiency. Detailed knowledge of flow patterns and aerodynamics loads is necessary for blade material and manufacturing process. In this study, an isolated propeller blade is chosen as the base of analysis, the geometry of the propeller: twist and chord variation with radius, are taken from real case module. The boundary conditions of the computational domain are set corresponding to that exist in the propeller manuals. A three dimensional unstructured grid was generated and adopted using commercial grid generator GAMBIT software. The governing equations are solved using FLUENT6.3.26 a commercial CFD code, which uses a control volume approach on a grid over the computational domain. Results identified that the propeller efficiency, power coefficient are increases to reach maximum values and then decreases with increase Mach number. The thrust coefficient decreases with increase Mach number.
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Wang, Zhitao, Jiayi Ma, Haichao Yu, and Tielei Li. "Research on Matching Characteristics of Ship-Engine-Propeller of COGAG." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59788.

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Abstract The combined gas turbine and gas turbine power propulsion device (COGAG power propulsion device) is an advanced combined power system, which uses multiple gas turbines as the main engine to drive propellers to propel the ship. COGAG power propulsion device has high power density, excellent stability and maneuverability, it receives more and more attention in the field of ship power at home and abroad. This article takes the COGAG power propulsion device as the research object, uses simulation methods to study its steady-state operating characteristics, and conducts a ship-engine-propeller optimization matching analysis based on economy and maneuverability. The research work carried out in this article is as follows. Firstly, according to the structural relationship between the various components and the system thermal cycle mode of the COGAG power propulsion device, establish the controller, main engine, gear box, clutch, shafting, propeller, ship and other components and simulation models of the system with the modular modeling idea. Secondly, divide the gears according to ship speed. For the four working modes of single-gas turbine with load, dual-gas turbine with load, three-gas turbine with load, and four-gas turbine with load, analysis the ship-engine-propeller optimization matching of the COGAG power propulsion device based on economy and maneuverability, and calculate the best shaft speed and propeller pitch ratio in each gear, so as to obtain the steady-state operation characteristics of the COGAG power propulsion device based on the ship-engine-propeller matching, which provides a basis for determining the target parameters of the dynamic process.
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Bellocq, Pablo, Vishal Sethi, Stefano Capodanno, Alexis Patin, and Fernando Rodriguez Lucas. "Advanced 0-D Performance Modelling of Counter Rotating Propellers for Multi-Disciplinary Preliminary Design Assessments of Open Rotors." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-27141.

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Due to their high propulsive efficiency, Counter Rotating Open Rotors (CRORs) have the potential to significantly reduce fuel consumption and emissions relative to conventional high bypass ratio turbofans. However, this novel engine architecture presents many design and operational challenges both at engine and aircraft level. The assessment of the impact of the main low pressure preliminary design and control parameters of CRORs on mission fuel burn, certification noise and emissions is necessary at preliminary design stages in order to identify optimum design regions. These assessments may also aid the development process when compromises need to be performed as a consequence of design, operational or regulatory constraints. The required preliminary design simulation tools should ideally be 0-D or 1-D (for computational purposes) and should capture the impact of the independent variation of the main low pressure system design and control variables such as: the number of blades, diameter and rotational speed of each propeller, the spacing between the propellers and the torque ratio of the gearbox or the counter rotating turbine amongst others. From a performance point of view, counter rotating propellers have historically been modelled as single propellers. Such a performance model does not provide the required flexibility for a detailed design and control study. This paper presents a novel 0-D performance model for Counter Rotating Propellers (CRPs) based on the classical low speed performance model for individual propellers and the interactions between them. This model also incorporates a compressibility correction which is applied to both propellers. The proposed model is verified with publicly available wind tunnel test data from NASA. The novel 0-D counter rotating propeller performance model is used to produce a performance model of a geared Open Rotor engine with a 10% clipped propeller. This engine model is first used to study the impact of the control of the propellers on the cruise fuel consumption. Subsequently, the engine performance model is integrated in a multi-disciplinary simulation platform to study the impact of the control of the propellers on the certification noise. The results of this case study show that 1–2% SFC savings at cruise are possible and an optimal control schedule is identified. It is also concluded that significant certification noise reductions are possible through an adequate control of the rotational speeds of the propellers.
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Prathapanayaka, Rajeevalochanam, Nanjundaiah Vinod Kumar, Krishnamurthy Settisara Janney, and Hari Krishna Nagishetty. "Design and Analysis Software for Propellers." In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3681.

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Recent interest in the field of micro and nano scale air vehicles attracted the attention of many researchers all over the world. The challenge associated with these classes of vehicles is to develop efficient miniaturized components. There are different types of micro and nano air vehicles out of which fixed wing micro air vehicle is one of them. Propulsion system for most of the fixed wing MAVs is propeller driven by an electric motor powered by a battery. The endurance of the MAV mainly depends on the performance of these two components. Hence there is a scope to improve the performance of the propeller and motor. Efficient propeller design and its performance analysis are an iterative process and time consuming. In the present study, to ease the process of propeller design and analysis NALPROPELLER code has been developed using MATLAB. This code is based on minimum induced loss theory presented by E.E.Larrabee to generate planform, blade element momentum theory along with Prandtl hub-tip loss model for overall performance analysis and the performance plots could be viewed in the GUI windows. The code consists of three modules namely single airfoil design, multi airfoil design and analysis module. This code is compared with one of the propeller design and analysis code available in the internet JavaProp by Martin Hepperle, which is also based on minimum induced loss method. From literature Eppler 193 airfoil show high lift to drag ratios at low Reynolds numbers [16]. Eppler-193 airfoil is used in the evaluation of propeller performance. A four inch diameter, two bladed, fixed pitch propeller is designed and analysed using this code. The design is compared with one of the design software JavaProp available online as an open source. A poly urethane casting propeller is fabricated based on the design. The performance comparison of the NALPROPELLER code, JavaProp and 3D CFD analysis is presented and discussed.
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Ghenaiet, Adel, and Akila Halimi. "Aerodynamic Characterization of a High Speed Propeller." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25765.

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This paper presents a numerical study aimed at characterizing the aerodynamics of an advanced propeller distinguished by its high rotational speed, blade sweep and airfoil sections. Many of the difficulties encountered when applying CFD to an open rotor (a propeller) arise due to removal of the casing existing in a conventional aero-engine turbomachinery. For this purpose the propeller computational domain needed to be well parameterized to keep sufficient outer domains distances where the appropriate boundary conditions are imposed. The mesh of a certain resolution was extended radially, five times the tip radii, to fully capture the stream-tube and minimize the effect of free-stream boundary conditions. Comparisons of obtained flow field results with some available experimental data shows in general similar quantitative results and trends. The estimated propulsive efficiency is shown to be strongly dependent upon the cruise flight Mach number, advance ratio and pitch angle. The maximum propulsive efficiency reached a value of 76.2 % around flight Mach number of 0.8, twist angle of 66 deg and advance ratio of 4.1. The effect of blades number has revealed a higher propulsive efficiency for the six and eight-bladed propellers but at the expense of lower power and thrust coefficients.
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Abbaszadeh, Morteza, Parvin Nikpour Parizi, and Ramin Taheri. "A Novel Approach to Design Reversible Counter Rotating Propeller Fans." In ASME 2012 Gas Turbine India Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gtindia2012-9657.

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Because of their high performance and unique abilities like producing none-rotating wake, Counter Rotating Propellers (C.R.P.) are being used in many advanced propulsion or ventilation systems. But due to complicated design procedure of C.R.P. fans up to now it was not possible to apply the concept in reversible systems. For the first time in this research, a new method presented to design a reversible counter rotating propeller system. This method is based on designing a basic C.R.P. by a reliable edition of blade element theory to achieve maximum performance in main rotating course and then to optimize it in order to have almost same performance in reverse rotating course. After expressing concepts of the method, a basic model is designed to ensure the capability of the presented scheme. Design outcome was a Reversible C.R.P. (R.C.R.P) system with 0.5 meter in diameter and cross section of NACA2412 airfoil. This model is evaluated by using R.S.M. turbulence method through ANSYS Fluent commercial software package. Evaluation results showed that system has efficiency of 0.85 in main course and 0.78 in reverse course by which a good performance for a small size reversible system can be captured.
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Tantot, Nicolas, Thierry Brichler, Matthieu Dubosc, and Sacha Ghebali. "Innovative Approaches to Propellers Off-Design Performance Modeling." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42145.

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This article provides an overview on the challenges related to the prediction of propellers performance at preliminary design stage, ranging from numerical stability to simplicity required for being integrated into engine cycle models. After a description of the usual approach to propeller performance based on maps, and a discussion on its limitations, innovative methods are proposed, lying on the identification of losses trends combined with the use of propeller characteristic operating points over the whole usable area. These innovative approaches significantly reduce the number of required simulations or test cell points to be able to describe the full propeller range of operation, adding physics to the mathematical approach usually considered for turbomachinery component maps elaboration. Accuracy and stability of the considered approaches are discussed, along with an assessment of the required effort to set them up.
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