Relevant bibliographies by topics / Turbomachines Design and construction

Contents

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

Academic literature on the topic 'Turbomachines Design and construction'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Turbomachines Design and construction"

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Żywica, Grzegorz, Tomasz Kaczmarczyk, Eugeniusz Ihnatowicz, Paweł Bagiński, and Artur Andrearczyk. "Design and Manufacturing of Micro-Turbomachinery Components with Application of Heat Resistant Plastics." Mechanics and Mechanical Engineering 22, no. 2 (August 24, 2020): 649–60. http://dx.doi.org/10.2478/mme-2018-0051.

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AbstractThe article discusses issues associated with the use of modern plastics for the construction of high-speed fluid-flow machines. Currently available plastics exhibit high chemical resistance as well as dimensional and shape stability across a wide temperature range. This allows them to be used for manufacturing components of micro turbomachinery, thereby reducing production time and costs. This article discusses the criteria for the selection of plastics suitable for a particular machine, namely micro turbogenerator operating in the organic Rankine cycle (ORC). In addition to the initial selection of materials based on their chemical and physical properties, strength calculations of selected turbogenerator subassemblies were carried out. The obtained results confirmed that some plastics can replace traditional materials used in the manufacture of ORC turbogenerators. This concerns, in particular, the components of the microturbine blade system. After the manufacture of a trial series of such components, it became apparent that, with appropriately chosen plastics, it is possible to shorten the machining time and reduce production costs, all while maintaining the required dimensional tolerances. The results obtained so far prove that it is possible to use plastics to produce components of modern turbomachines, for instance, parts of high-speed microturbines that have to withstand high operating temperatures.
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Sazonov, Yuri A., Mikhail A. Mokhov, Inna V. Gryaznova, Victoria V. Voronova, Khoren A. Tumanyan, Mikhail A. Frankov, and Nikolay N. Balaka. "Computational Fluid Dynamics (CFD) Simulation of Mesh Jet Devices for Promising Energy-Saving Technologies." Civil Engineering Journal 8, no. 12 (December 1, 2022): 2749–67. http://dx.doi.org/10.28991/cej-2022-08-12-06.

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This paper discusses the development of mesh jet devices for hybrid turbines, including developing Euler's ideas, and considers a new patented version of a mesh jet device designed to create guiding devices for turbines. The research methods are based on simulations using CFD and additive technologies. An intermediate conclusion is that a new scientific direction for the study and creation of mesh jet control systems has been formed as part of developing Euler's ideas. Calculation methods showed possible improvements in the performance of jet devices, including the use of curved tubes proposed by Euler to create turbines. This study shows that at the nozzle or mixing chamber outlet, the jet can deflect by an angle from +180° to -180° within the geometric sphere. This study also shows that the scientific groundwork prepared by Euler is not yet fully understood. The ongoing research mainly focuses on creating multi-mode jet devices designed for control systems for mesh turbomachines. Here, power consumption from an external source can be reduced to save energy. Some results of ongoing studies can also be applied in other industries (for example, when creating hybrid propulsion systems or propulsors). The scientific novelty of this work consists of improving the design methodology of jet machinery and turbomachines. Doi: 10.28991/CEJ-2022-08-12-06 Full Text: PDF
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Sazonov, Yuri Appolonievich, Mikhail A. Mokhov, Inna Vladimirovna Gryaznova, Victoria Vasilievna Voronova, Khoren Arturovich Tumanyan, Mikhail Alexandrovich Frankov, and Nikolay Nikolaevich Balaka. "Designing Mesh Turbomachinery with the Development of Euler’s Ideas and Investigating Flow Distribution Characteristics." Civil Engineering Journal 8, no. 11 (November 1, 2022): 2598–627. http://dx.doi.org/10.28991/cej-2022-08-11-017.

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This research discusses developing an Euler turbine-based hybrid mesh turbomachinery. Within the framework of mechanical engineering science, turbomachinery classification and a novel method for mesh turbomachinery design were considered. In such a turbomachine, large blades are replaced by a set of smaller blades, which are interconnected to form flow channels in a mesh structure. Previous studies (and reasoning within the framework of inductive and deductive logic) showed that the jet mesh control system allows for operation with several flows simultaneously and provides a pulsed flow regime in flow channels. This provides new opportunities for expanding the control range and reducing the thermal load on the turbomachine blades. The novel method for performance evaluation was confirmed by the calculation: the possibility of implementing pulsed cooling of blades periodically washed by a hot working gas flow (at a temperature of 1000°C) and a cold gas flow (at a temperature of 20°C) was shown. The temperature of the blade walls remained 490–525°C. New results of ongoing research are focused on creating multi-mode turbomachinery that operates in complicated conditions, e.g., in offshore gas fields. Gas energy is lost and dissipated in the throttle at the mouth of each high-pressure well. Within the framework of ongoing research, the environmentally friendly net reservoir energy of high-pressure well gas should be rationally used for operating a booster compressor station. Here, the energy consumption from an external power source can be reduced by 50%, according to preliminary estimates. Doi: 10.28991/CEJ-2022-08-11-017 Full Text: PDF
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Silva, E. Raimunda da, R. G. R. Camacho, and N. M. Filho. "Global optimization based on metamodel construction app lied to design axial turbomachinery cascades using CFD." IOP Conference Series: Earth and Environmental Science 12 (August 1, 2010): 012095. http://dx.doi.org/10.1088/1755-1315/12/1/012095.

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Demelio, G. P., SM Camporeale, A. Castellano, F. Cupertino, and M. Torresi. "Design and construction of an offshore diffuser augmented wind turbine with a high efficiency alternator." IOP Conference Series: Materials Science and Engineering 1214, no. 1 (January 1, 2022): 012030. http://dx.doi.org/10.1088/1757-899x/1214/1/012030.

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Abstract This paper describes the design and the assembly of a new type of a ducted wind turbine with an electric power generator adopting permanent high coercive magnets embedded in the peripheral ring of the rotor. The nominal power is 20 kW, and the maximum diameter of the external duct is 9 meters. The project has been carried out within the Marine Energy Laboratory (MEL) funded by the Italian Ministry for Education, University and Research (MIUR) and collects the most advanced technologies of naval maritime engineering and combines them with energy and turbomachinery technologies. The presence of a divergent duct enables the interception of a greater air mass flow rate, allowing the reduction of the rotor diameter and the deflections of the blades; hence, at constant tip speed ratio, a higher rotational speed compared to conventional turbines and a better efficiency of the permanent magnet power generator.
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Korakianitis, T. "Prescribed-Curvature-Distribution Airfoils for the Preliminary Geometric Design of Axial-Turbomachinery Cascades." Journal of Turbomachinery 115, no. 2 (April 1, 1993): 325–33. http://dx.doi.org/10.1115/1.2929238.

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Blade surfaces with continuous curvature and continuous slope of curvature minimize the possibility of flow separation, lead to improved blade designs, and reduce the direct and inverse blade-design iterations for the selection of isolated airfoils and gas-turbine-blade cascades. A method for generating two-dimensional blade shapes is presented. The geometry near the trailing edge is specified by an analytic polynomial, the main portion of the blade surface is mapped using as input a prescribed surface-curvature distribution, and the leading edge is specified as a thickness distribution added to a construction line. This procedure is similar for the suction and pressure surfaces, and by specification it constructs continuous slope-of-curvature surfaces that result in smooth surface-Mach-number and surface-pressure distributions. The method can be used to generate subsonic or supersonic airfoils for compressors and turbines, or isolated airfoils. The resulting geometric shapes can be used as inputs to various blade-design sequences. It is shown that, with other cascade-design parameters being equal, increasing the stagger angle of turbine blades results in more front-loaded and thinner blades, and that there is an optimum stagger angle resulting in minimum wake thickness. The subsonic axial-turbine blade rows included for discussion in this paper have been designed by iterative modifications of the blade geometry to obtain a desirable velocity distribution. The blade-design method can be used to improve the aerodynamic and heat transfer performance of turbine cascades, and it can result in high-performance airfoils, even if using the direct method exclusively, in very few iterations.
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Korakianitis, T. "Hierarchical Development of Three Direct-Design Methods for Two-Dimensional Axial-Turbomachinery Cascades." Journal of Turbomachinery 115, no. 2 (April 1, 1993): 314–24. http://dx.doi.org/10.1115/1.2929237.

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The direct and inverse blade-design iterations for the selection of isolated airfoils and gas turbine blade cascades are enormously reduced if the initial blade shape has performance characteristics near the desirable ones. This paper presents the hierarchical development of three direct blade-design methods of increasing utility for generating two-dimensional blade shapes. The methods can be used to generate inputs to the direct- or inverse-blade-design sequences for subsonic or supersonic airfoils for compressors and turbines, or isolated airfoils. The examples included for illustration are typical modern turbine cascades, and they have been designed by the direct method exclusively. The first method specifies the airfoil shapes with analytical polynomials. It shows that continuous curvature and continuous slope of curvature are necessary conditions to minimize the possibility of flow separation, and to lead to improved blade designs. The second method specifies the airfoil shapes with parametric fourth-order polynomials, which result in continuous-slope-of-curvature airfoils, with smooth Mach number and pressure distributions. This method is time consuming. The third method specifies the airfoil shapes by using a mixture of analytical polynomials and mapping the airfoil surfaces from a desirable curvature distribution. The third method provides blade surfaces with desirable performance in very few direct-design iterations. In all methods the geometry near the leading edge is specified by a thickness distribution added to a construction line, which eliminates the leading edge overspeed and laminar-separation regions. The blade-design methods presented in this paper can be used to improve the aerodynamic and heat transfer performance of turbomachinery cascades, and they can result in high-performance airfoils in very few iterations.
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Kidd, S. R., J. S. Barton, P. Meredith, J. D. C. Jones, M. A. Cherrett, and K. S. Chana. "A Fiber Optic Probe for Gas Total Temperature Measurement in Turbomachinery." Journal of Turbomachinery 117, no. 4 (October 1, 1995): 635–41. http://dx.doi.org/10.1115/1.2836582.

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This paper describes the design, operation, construction, and demonstration of a new type of high-bandwidth unsteady temperature sensor based on fiber optics, and capable of operating in a high-speed multistage research compressor with flow representative of jet engine conditions. The sensing element is an optical coating of zinc selenide deposited on the end of an optical fiber. During evaluation in aerodynamic testing, a 1 K gas temperature resolution was demonstrated at 9.6 kHz and an upper bandwidth limit of 36 kHz achieved.
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Siddappaji, Kiran, and Mark G. Turner. "Versatile Tool for Parametric Smooth Turbomachinery Blades." Aerospace 9, no. 9 (August 31, 2022): 489. http://dx.doi.org/10.3390/aerospace9090489.

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Designing blades for efficient energy transfer by turning the flow and angular momentum change is both an art and iterative multidisciplinary engineering process. A robust parametric design tool with few inputs to create 3D blades for turbomachinery and rotating or non-rotating energy converters is described in this paper. The parameters include axial–radial coordinates of the leading/trailing edges, construction lines (streamlines), metal angles, thickness-to-chord ratio, standard, and user-defined airfoil type among others. Using these, 2D airfoils are created, conformally mapped to 3D stream surfaces, stacked radially with multiple options, and they are transformed to a 3D Cartesian coordinate system. Smooth changes in blade curvature are essential to ensure a smooth pressure distribution and attached flow. B-splines are used to control meanline curvature, thickness, leading edge shape, sweep-lean, and other parameters chordwise and spanwise, making the design iteration quick and easy. C2 curve continuity is achieved through parametric segments of cubic and quartic B-splines and is better than G2. New geometries using an efficient parametric scheme and minimal CAD interaction create watertight solid bodies and optional fluid domains. Several examples of ducted axial and radial turbomachinery with special airfoil shapes or otherwise, unducted rotors including propellers and wind and hydrokinetic turbines are presented to demonstrate versatility and robustness of the tool and can be easily tied to any automation chain and optimizer.
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Morgese, Gaetano, Francesco Fornarelli, Paolo Oresta, Tommaso Capurso, Michele Stefanizzi, Sergio M. Camporeale, and Marco Torresi. "Fast Design Procedure for Turboexpanders in Pressure Energy Recovery Applications." Energies 13, no. 14 (July 16, 2020): 3669. http://dx.doi.org/10.3390/en13143669.

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Sustainable development can no longer neglect the growth of those technologies that look at the recovery of any energy waste in industrial processes. For example, in almost every industrial plant it happens that pressure energy is wasted in throttling devices for pressure and flow control needs. Clearly, the recovery of this wasted energy can be considered as an opportunity to reach not only a higher plant energy efficiency, but also the reduction of the plant Operating Expenditures (OpEx). In recent years, it is getting common to replace throttling valves with turbine-based systems (tuboexpander) thus getting both the pressure control and the energy recovery, for instance, producing electricity. However, the wide range of possible operating conditions, technical requirements and design constrains determine highly customized constructions of these turboexpanders. Furthermore, manufacturers are interested in tools enabling them to rapidly get the design of their products. For these reasons, in this work we propose an optimization design procedure, which is able to rapidly come to the design of the turboexpander taking into account all the fluid dynamic and technical requirements, considering the already obtained achievements of the scientific community in terms of theory, experiments and numeric. In order to validate the proposed methodology, the case of a single stage axial impulse turbine is considered. However, the methodology extension to other turbomachines is straightforward. Specifically, the design requirements were expressed in terms of maximum allowable expansion ratio and flow coefficient, while achieving at least a minimum assigned value of the turbine loading factor. Actually, it is an iterative procedure, carried out up to convergence, made of the following steps: (i) the different loss coefficients in the turbine are set-up in order to estimate its main geometric parameters by means of a one dimensional (1D) study; (ii) the 2D blade profiles are designed by means of an optimization algorithm based on a “viscous/inviscid interaction” technique; (iii) 3D Computational Fluid Dynamic (CFD) simulations are then carried out and the loss coefficients are computed and updated. Regarding the CFD simulations, a preliminary model assessment has been performed against a reference case, chosen in the literature. The above-mentioned procedure is implemented in such a way to speed up the convergence, coupling analytical integral models of the 1D/2D approach with accurate local solutions of the finite-volume 3D approach. The method is shown to be able to achieve consistent results, allowing the determination of a turbine design respectful of the requirements more than doubling the minimum required loading factor.
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Dissertations / Theses on the topic "Turbomachines Design and construction"

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Shrinivas, Gorur N. "Three-dimensional design methods for turbomachinery applications." Thesis, University of Oxford, 1996. http://ora.ox.ac.uk/objects/uuid:8ace58b5-e251-491e-9753-ae8b236d6c3b.

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This thesis studies the application of sensitivity analysis and optimization methods to the design of turbomachinery components. Basic design issues and a survey of current design trends are presented. The redesign of outlet guide vanes (OGV's) in an aircraft high bypass turbofan engine is attempted. The redesign is necessitated by the interaction of the pylon induced static pressure field with the OGV's and the fan, leading to reduced OGV efficiency and shortened fan life. The concept of cyclically varying camber is used to redesign the OGV row to achieve suppression of the downstream disturbance in the domain upstream of the OGV row. The redesign is performed using (a) a linear perturbation CFD analysis and (b) a minimisation of the pressure mismatch integral by using a Newton method. In method (a) the sensitivity of the upstream flow field to changes in blade geometry is acquired from the linear perturbation CFD analysis, while in method (b) it is calculated by perturbing the blade geometry and differencing the resulting flow fields. Method (a) leads to a reduction in the pylon induced pressure variation at the fan by more than 70% while method (b) achieves up to 86%. An OGV row with only 3 different blade shapes is designed using the above method and is found to suppress the pressure perturbation by more than 73%. Results from these calculations are presented and discussed. The quasi-Newton design method is also used to redesign a three dimensional OGV row and achieves considerable reduction of upstream pressure variation. A concluding discussion summarises the experiences and suggests possible avenues for further work.
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Klostermeier, Christian. "Investigation into the capability of large eddy simulation for turbomachinery design." Thesis, University of Cambridge, 2008. https://www.repository.cam.ac.uk/handle/1810/252106.

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Engin, Ertan. "Design, Construction And Performance Evaluation Of A Submersible Pump With Numerical Experimentation." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/12606532/index.pdf.

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Due to the increasing demand, nonclog type sewage pumps are designed and manufactured in large amounts all over the world. However, a methodology on the design of these special duty pumps is not encountered in the literature. Therefore, the manufacturers tend to develop their own empirical methodologies. In this thesis, a nonclog pump is designed and constructed on the basis of suitable approaches of known centrifugal pump design methods. In this frame, a nonclog type submersible pump that is capable of handling solids, up to a diameter of 80 mm is aimed to be designed. The designed pump delivers 100 l/s flow rate against a head of 24 m. The rotational speed of the pump is 1000 rpm. Design procedure and the important points that differ nonclog pump design from standard centrifugal pump designs are given. In addition, hydraulic characteristics of two nonclog pumps, one of which is the pump designed in this study, are investigated by means of computational fluid dynamics (CFD) code. The designed pump is manufactured and tested in Layne Bowler Pump Company Inc. The test result indicates that design point is reached with a deviation in the limits of the related standard. Wire to water total best efficiency obtained by the test is 60%. Close agreement between results of actual test and numerical experimentation performed by CFD code shows that CFD analysis is a quite useful tool in predicting the hydraulic characteristics of nonclog pumps. Moreover, the pump is tested at 750 rpm and the test results are found to be in good agreement with the similitude anaysis results.
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Suhr, Stephen Andrew. "Preliminary Turboshaft Engine Design Methodology for Rotorcraft Applications." Thesis, Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14128.

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In the development of modern rotorcraft vehicles, many unique challenges emerge due to the highly coupled nature of individual rotorcraft design disciplines therefore, the use of an integrated product and process development (IPPD) methodology is necessary to drive the design solution. Through the use of parallel design and analysis, this approach achieves the design synthesis of numerous product and process requirements that is essential in ultimately satisfying the customers demands. Over the past twenty years, Georgia Techs Center for Excellence in Rotorcraft Technology (CERT) has continuously focused on refining this IPPD approach within its rotorcraft design course by using the annual American Helicopter Society (AHS) Student Design Competition as the design requirement catalyst. Despite this extensive experience, however, the documentation of this preliminary rotorcraft design approach has become out of date or insufficient in addressing a modern IPPD methodology. In no design discipline is this need for updated documentation more prevalent than in propulsion system design, specifically in the area of gas turbine technology. From an academic perspective, the vast majority of current propulsion system design resources are focused on fixed-wing applications with very limited reference to the use of turboshaft engines. Additionally, most rotorcraft design resources are centered on aerodynamic considerations and largely overlook propulsion system integration. This research effort is aimed at bridging this information gap by developing a preliminary turboshaft engine design methodology that is applicable to a wide range of potential rotorcraft propulsion system design problems. The preliminary engine design process begins by defining the design space through analysis of the initial performance and mission requirements dictated in a given request for proposal (RFP). Engine cycle selection is then completed using tools such as GasTurb and the NASA Engine Performance Program (NEPP) to conduct thorough parametric and engine performance analysis. Basic engine component design considerations are highlighted to facilitate configuration trade studies and to generate more detailed engine performance and geometric data. Throughout this approach, a comprehensive engine design case study is incorporated based on a two-place, turbine training helicopter known as the Georgia Tech Generic Helicopter (GTGH). This example serves as a consistent propulsion system design reference highlighting the level of integration and detail required for each step of the preliminary turboshaft engine design methodology.
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Fowler, Andrew. "A new advanced turbine-stage test facility : the concept, design, construction and commissioning." Thesis, University of Oxford, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.386786.

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Yoo, Hanyung. "A computational package to aid the design and to evaluate centrifugal turbopumps /." Online version of thesis, 1995. http://hdl.handle.net/1850/12289.

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Ragula, Vivian Vineeth Raj. "Streamline based Analysis and Design Technique for Turbomachines." University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1304022216.

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DiPietro, Anthony Louis. "Design and experimental evaluation of a dynamic thermal distortion generator for turbomachinery research." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-09292009-020206/.

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Wissinger, Gordon J. "Computational analysis of space transfer vehicle engine turbopump diffuser design for deep-throttling : by Gordon J. Wissinger /." Online version of thesis, 1991. http://hdl.handle.net/1850/11001.

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Jouini, Dhafer Ben Mahmoud Carleton University Dissertation Engineering Mechanical and Aerospace. "Experimental investigation of two transonic linear turbine cascades at off-design conditions." Ottawa, 2000.

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Books on the topic "Turbomachines Design and construction"

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Whitfield, A. Design of radial turbomachines. Harlow, Essex, England: Longman Scientific & Technical, 1990.

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Round, G. F. Incompressible flow turbomachines: Design, selection, applications, and theory. Amsterdam: Elsevier, 2004.

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Chen, Naixing. Aerothermodynamics of turbomachinery: Analysis and design. Hoboken, N.J: Wiley, 2010.

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Wislicenus, George F. Preliminary design of turbopumps and related machinery. [Cleveland, Ohio]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Wislicenus, George F. Preliminary design of turbopumps and related machinery. Washington, D.C: NASA, Scientific and Technical Information Branch, 1986.

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IMP '97 Conference on Modeling and Design in Fluid-Flow Machinery (1997 Gdańsk, Poland). Modeling and design in fluid-flow machinery, 1997: Proceedings of the IMP '97 Conference on Modeling and Design in Fluid-Flow Machinery, Gdańsk, November 18-21, 1997. Edited by Badur J and Polska Akademia Nauk. Instytut Maszyn Przepływowych. Gdańsk: Wydawn. IMP PAN, 1997.

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Wilson, David Gordon. The design of high-efficiency turbomachinery and gas turbines. 2nd ed. Upper Saddle River, N.J: Prentice Hall, 1998.

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Parsons International Turbine Conference (2nd 1984 Churchill College). Materials development in Turbo-machinery design: Second Parsons International Turbine Conference. London: Institute of Metals, 1989.

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Wilson, David Gordon. The design of high-effiency turbomachinery and gas turbines. 2nd ed. Upper Saddle River, N.J: Prentice Hall, 1998.

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Doeuff, R. Le. Electrical rotating machines: From matrix modeling to implementation. London: ISTE, 2009.

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Book chapters on the topic "Turbomachines Design and construction"

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Schobeiri, Meinhard T. "Efficiency of Multi-Stage Turbomachines." In Gas Turbine Design, Components and System Design Integration, 213–23. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-58378-5_7.

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Schobeiri, Meinhard T. "Efficiency of Multi-Stage Turbomachines." In Gas Turbine Design, Components and System Design Integration, 215–24. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-23973-2_7.

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Maisel, Jordana L., Edward Steinfeld, Megan Basnak, Korydon Smith, and M. Beth Tauke. "Construction." In Inclusive Design, 97–124. New York : Routledge, 2017. | Series: PocketArchitecture : technical design series: Routledge, 2017. http://dx.doi.org/10.4324/9781315712437-4.

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Chappell, David. "Design." In Construction Contracts, 90–102. Fourth edition. | Abingdon, Oxon; New York: Routledge, 2021.: Routledge, 2020. http://dx.doi.org/10.1201/9781003080930-10.

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Chappell, David. "Design." In Construction Contracts, 90–102. Fourth edition. | Abingdon, Oxon; New York: Routledge, 2021.: Routledge, 2020. http://dx.doi.org/10.4324/9781003080930-10.

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Beadnall, Stuart, and Simon Moore. "Design risk." In Offshore Construction, 47–72. 2nd ed. London: Informa Law from Routledge, 2021. http://dx.doi.org/10.4324/9780367855574-3.

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Mosley, W. H., J. H. Bungey, and R. Hulse. "Composite construction." In Reinforced Concrete Design, 350–73. London: Macmillan Education UK, 1999. http://dx.doi.org/10.1007/978-1-349-14911-7_13.

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McLean, Will, and Pete Silver. "Construction Technology." In Environmental Design Sourcebook, 66–97. London: RIBA Publishing, 2021. http://dx.doi.org/10.4324/9781003189046-3.

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Houben, Hugo, and Hubert Guillard. "10. Design Guidelines." In Earth Construction, 244–303. Rugby, Warwickshire, United Kingdom: Practical Action Publishing, 1989. http://dx.doi.org/10.3362/9781780444826.010.

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Soutsos, Marios, and Peter Domone. "Concrete mix design." In Construction Materials, 249–58. Fifth edition. | Boca Raton : CRC Press, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315164595-25.

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Conference papers on the topic "Turbomachines Design and construction"

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Mu¨ller, N., B. Lindberg, M. Mouland, N. Holden, A. Lahiri, and B. Wagenknecht. "Low-Cost Wound and Woven Composite Turbomachinery Design." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27692.

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A novel design and manufacturing of light-weight high-strength composite impellers with integrated motor and bearing is introduced. It is based on winding or weaving endless fiber material on a commercially available winder. This concept may be applied for compressors, pumps, turbines, propellers, or jet propulsion devices (Fig. 1). By interweaving electrical motor components, constructions without a shaft, or shaft sealing are possible. Also, the active motor elements can be positioned outside of the fluid stream. Besides the low cost of construction, one of the main advantages to this design is the integration of electrical motors in the turbo-wheels. This allows for the easy implementation of multiple counter-rotating turbomachinery stages in not only axial configurations, but also mixed flow configurations as well. The integrated motors are typically variable speed motors.
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Merchant, Ali, and Robert Haimes. "A CAD-Based Blade Geometry Model for Turbomachinery Aero Design Systems." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38305.

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A CAD-centric approach for constructing and managing the blade geometry in turbomachinery aero design systems is presented in this paper. Central to the approach are a flexible CAD-based parametric blade model definition and a set of CAD-neutral interfaces which enable construction and manipulation of the blade solid model directly inside the CAD system’s geometry kernel. A bottleneck of transferring geometry data passively via a file-based method is thus eliminated, and a seamless integration between the CAD system, aero design system, and the larger design environment can be achieved. A single consistent CAD-based blade model is available at all stages of the aero design process, forming the basis for coupling the aero design system to the larger multi-disciplinary design environment. The blade model construction is fully parameterized so that geometry updates can be accurately controlled via parameter changes, and geometric sensitivities of the model can be easily calculated for multidisciplinary interaction and design optimization. A clear separation of the parameters that control the three-dimensional shape of the blade (such as lean and sweep) from the parameters that control the elemental profile shape allows any blade profile family or shape definition to be utilized. The blade model definition, construction interface, and implementation approach are described. Applications illustrating solid model construction, parametric modification and sensitivity calculation, which are key requirements for automated aerodynamic shape design, are presented.
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Batailly, Alain, Mathias Legrand, Patrice Cartraud, Christophe Pierre, and Jean-Pierre Lombard. "Study of Component Mode Synthesis Methods in a Rotor-Stator Interaction Case." In ASME 2007 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/detc2007-34781.

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The study of rotor-stator interactions between blade-tips and outer casings through direct contact in modern turbomachines is very time-consuming if the classical finite element method is used. In order to improve the knowledge over these interaction phenomena, faster methods have to be applied. The construction of reduced-order models using component mode synthesis methods generally allows for dramatic increase in computational efficiency. Two of these methods, namely a fixed interface method and a free interface methods are considered in an original manner to reduce the size of a realistic two-dimensional model. They are then compared in a very specific contact case-study. The equations of motion are solved using an explicit time integration scheme with the Lagrange multiplier method where friction is accounted for. The primary goal of the present study is to investigate the general behavior of such approaches in the presence of contact nonlinearities. It will be shown that in our contact case, a good accuracy can be obtained from a reduced models with very limited number of modes.
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Nachtigal, Philipp, Thorge Kentschke, and Joerg R. Seume. "Experimentally Validated Design of an Anode Recirculation Blower for PEM Fuel Cells Under Variable Fluid Composition." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-80525.

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Abstract This paper focuses on the design, construction and the experimental testing of an anode recirculation blower (ARB) based on a turbo-compressor for PEM-FCs. The blower presented consists of a high-speed centrifugal compressor, driven by a so-called media-gap motor. Additionally it includes a droplet separator to eliminate liquid water from the anode loop. The aerodynamic design is based on 1D-correlations and 3D-numerical CFD simulations. Different gas compositions of hydrogen, nitrogen and water vapor are considered in the design, depending on the operating points of a PEM-FC. The gas composition has a significant influence on the achievable pressure ratio at constant compressor speeds, depending mainly on the specific heat capacity of the gas. Performance maps for different gas compositions are calculated using CFD for the designed ARB. A prototype is built and tested. The results validate the CFD predictions and show that the operating range of a PEM fuel cell can be covered with the present blower. In addition, it could be shown that an enthalpy-based approach using common characteristic numbers of turbomachines, allows converting performance maps — acquired with different gas compositions — into one another. This allows the performance map prediction for different gas compositions based on existing performance maps. This approach is illustrated by numerical and experimental results.
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Barton, J. S., J. M. Kilpatrick, W. N. MacPherson, J. D. C. Jones, K. S. Chana, J. S. Anderson, D. R. Buttsworth, and T. V. Jones. "Optical Fibre Aerodynamic Probes for Total Pressure and Total Temperature Measurement in Turbomachinery." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-308.

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Optical fibre sensors offer the prospect of miniature aerodynamic probes for highly localised flow measurements in aerospace wind tunnels and turbomachines. We discuss the design and construction of optical fibre sensors for temperature and pressure. The temperature sensors consist of multilayer coatings deposited on the fibre end face from which the reflected intensity is temperature-dependent. Two sensors were incorporated in a dual heated probe to measure total temperature. The pressure sensors are miniature diaphragms in which pressure-induced deflection is measured interferometrically in reflection. We present results from initial trials made in unsteady flow in a single stage research turbine, in which total temperature data with harmonic components up to 30 kHz and total pressure signals up to 230 kHz were recorded.
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Batailly, Alain, Mathias Legrand, Patrice Cartraud, Christophe Pierre, and Jean-Pierre Lombard. "Evaluation of Component Mode Synthesis Methods for the Detection of Modal Interaction Through Rotor Stator Contacts." In ASME 2009 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/detc2009-87036.

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The study of interactions through direct contact between bladetips and outer casings in modern turbomachines may be very time-consuming when the classical finite element method is used. The construction of reduced-order models using component mode synthesis (CMS) methods generally allows for dramatic increase in computational efficiency and may be used in order to improve the knowledge over these interaction phenomena. Among the available approaches, both a fixed-interface method and a free-interface method are considered here in an original manner to reduce the size of a realistic two-dimensional model. The equations of motion are solved using an explicit time integration scheme with the Lagrange multiplier method where friction is accounted for. This method offers energy momentum conserving which is a critical point to ensure the convergence of the algorithm. Moreover, it is shown that even in a non-linear framework the reduced-order models converge to the finite element solution as the number of modes included in the models increases. Considering the fixed-interface method of Craig-Bampton (CB) and the free-interface method of Craig-Chang-Martinez (CCM), it is shown that a method with fast displacement convergence may be less efficient in terms of motion convergence.
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Gary, Keith, Bugra Ertas, and Adolfo Delgado. "A General-Purpose Test Facility for Evaluating Gas Lubricated Thrust Bearings." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15520.

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Abstract The design, construction, operational capabilities, and proof of concept results are presented for a test rig used to evaluate gas-lubricated thrust bearings. The following work is motivated by a desire to utilize the working fluid of high-performance turbomachinery, such as gas turbines, for bearing lubricant. Auxiliary equipment required to cool, pump, and clean oil for a typical thrust bearing is eliminated by taking advantage of the turbomachinery’s working fluid as bearing lubricant. The benefit of removing such auxiliary equipment is obvious when considering cost and weight of turbomachines, yet the working fluid of gas turbines typically has very low viscosity compared to oil which introduces load capacity and stability challenges. It is therefore necessary to build a facility capable of testing gas-lubricated thrust bearings to advance the technology. The test rig design in this work allows for 7 to 15 inch (180–380 mm) diameter thrust bearings, static loads up to 30,000 lbf (135 kN), and speeds up to 20 krpm. The test facility also provides up to 500 psig (3.45 MPa) static air pressure to enable testing of hydrostatic and hybrid (hydrodynamic combined with hydrostatic) bearings. This paper describes the test rig operating principle, details experimental procedures to obtain measurements, and provides test results necessary to prove the test rig concept by means of a hybrid gas bearing.
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Gra¨sel, Ju¨rgen, Akin Keskin, Marius Swoboda, Hans Przewozny, and Andre´ Saxer. "A Full Parametric Model for Turbomachinery Blade Design and Optimisation." In ASME 2004 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/detc2004-57467.

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This paper presents a full parametric model of a turbomachinery blade. The model forms the geometric backbone of a new aerodynamic design suite, which aims at speeding up the coupled 2D/3D aerodynamic design process. The approach employed here follows the basic design concepts of turbomachinery blades, which are typically defined by a series of cross-sectional aerofoils stacked at their radial location to a three-dimensional blade. Unlike the geometry management in current design systems, the paradigm of a CAD based Master Model has been incorporated in the geometry definition and the corresponding software architecture. Therefore all blade features have been modelled as computational components in the flexible object-oriented software environment. The blade parameterisation enables the 2D aerofoil construction either from the common superposition of the camber line and thickness distribution or the direct control of the suction and pressure side. The sensitivity of the aerofoil aerodynamic performance with respect to a design parameter can be quickly assessed with a fast 2D flow solver. The parameters of the radial stacking line define the axial and tangential shift of each section. The parametric concept facilitates the inclusion of specific shape control techniques such as curvature manipulation and surface smoothing. Furthermore the use of optimisation methods is greatly simplified by the modular program structure, which allows to access single modules of the blade design tool in a batch job. Since the blade design process involves different coordinate systems, unique mapping functions are essential for a consistent update of the blade geometry during a design cycle. The interface to the CAD system is based on the standard data exchange format STEP. The CFD interface makes use of the NetCDF data format for automatic grid generation.
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Korakianitis, Theodosios. "Prescribed-Curvature-Distribution Airfoils for the Preliminary Geometric Design of Axial-Turbomachinery Cascades." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-366.

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Blade surfaces with continuous curvature and continuous slope of curvature minimize the possibility of flow separation, lead to improved blade designs, and reduce the direct and inverse blade-design iterations for the selection of isolated airfoils and gas-turbine-blade cascades. A method for generating two-dimensional blade shapes is presented. The geometry near the trailing edge is specified by an analytic polynomial, the main portion of the blade surface is mapped using as input a prescribed surface-curvature distribution, and the leading edge is specified as a thickness distribution added to a construction line. This procedure is similar for the suction and pressure surfaces, and by specification it constructs continuous slope-of-curvature surfaces that result in smooth surface-Mach-number and surface-pressure distributions. The method can be used to generate subsonic or supersonic airfoils for compressors and turbines, or isolated airfoils. The resulting geometric shapes can be used as inputs to various blade-design sequences. It is shown that, with other cascade-design parameters being equal, increasing the stagger angle of turbine blades results in more-front-loaded and thinner blades, and that there is an optimum stagger angle resulting in minimum wake thickness. The subsonic axial-turbine blade rows included for discussion in this paper have been designed by iterative modifications of the blade geometry to obtain a desirable velocity distribution. The blade-design method can be used to improve the aerodynamic and heat transfer performance of turbine cascades, and it can result in high-performance airfoils, even if using the direct method exclusively, in very few iterations.
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Sullivan, Shaun D., Jason Farias, James Kesseli, and James Nash. "Mechanical Design and Validation Testing for a High-Performance Supercritical Carbon Dioxide Heat Exchanger." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63639.

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Supercritical carbon dioxide (sCO2) Brayton cycles hold great promise as they can achieve high efficiencies — in excess of 50% — even at relatively moderate temperatures of 700–800 K. However, this high performance is contingent upon high-effectiveness recuperating and heat rejection heat exchangers within the cycle. A great deal of work has gone into development of these heat exchangers as they must operate not only at elevated temperatures and very high pressures (20–30 MPa), but they must also be compact, low-cost, and long-life components in order to fully leverage the benefits of the sCO2 power cycle. This paper discusses the mechanical design and qualification for a novel plate-fin compact heat exchanger designed for sCO2 cycle recuperators and waste heat rejection heat exchangers, as well as direct sCO2 solar absorber applications. The architecture may furthermore be extended to other very high pressure heat exchanger applications such as pipeline natural gas and transcritical cooling cycles. The basic heat exchanger construction is described, with attention given to those details which have a direct impact on the durability of the unit. Modeling and analysis of various mechanical failure modes — including burst strength, creep, and fatigue — are discussed. The design and construction of test sections, test rigs, and testing procedures are described, along with the test results that demonstrate that the tested design has an operating life well in excess of the 100,000 cycles/90,000 hour targets. Finally, the application of these findings to a set of design tools for future units is demonstrated.
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Reports on the topic "Turbomachines Design and construction"

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CORPS OF ENGINEERS WASHINGTON DC. Construction: Design and Construction Evaluation (DCE). Fort Belvoir, VA: Defense Technical Information Center, February 1996. http://dx.doi.org/10.21236/ada404141.

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Slocum, Alexander H., Laura A. Demsetz, David H. Levy, and Bruce Schena. Design Methodology for Automated Construction Machines. Fort Belvoir, VA: Defense Technical Information Center, December 1987. http://dx.doi.org/10.21236/ada207386.

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Fanella, David A., Amaldo T. Derecho, and S. K. Ghosh. Design and construction of structural systems. Gaithersburg, MD: National Institute of Standards and Technology, 2005. http://dx.doi.org/10.6028/nist.ncstar.1-1av1.

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Collins, James J. Design and Construction of Genetic Applets. Fort Belvoir, VA: Defense Technical Information Center, May 2003. http://dx.doi.org/10.21236/ada417910.

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Jackson, J. G. Y-12 Sustainable Design Principles for Building Design and Construction. Office of Scientific and Technical Information (OSTI), November 2008. http://dx.doi.org/10.2172/969028.

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CORPS OF ENGINEERS WASHINGTON DC. Engineering and Design. Construction with Large Stone. Fort Belvoir, VA: Defense Technical Information Center, October 1990. http://dx.doi.org/10.21236/ada402849.

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McNeese, L. E. ORNL engineering design and construction reengineering report. Office of Scientific and Technical Information (OSTI), January 1998. http://dx.doi.org/10.2172/631227.

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Janet E.R. Mcllvaine, David Beal, and Philip Fairey. INTERIOR DUCT SYSTEM DESIGN, CONSTRUCTION, AND PERFORMANCE. Office of Scientific and Technical Information (OSTI), October 2001. http://dx.doi.org/10.2172/823970.

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Schwartztrauber, K. Modular Design/Phased Construction Alternative Evaluation Report. Office of Scientific and Technical Information (OSTI), May 1999. http://dx.doi.org/10.2172/763136.

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Deschamps, Richard, Christopher Hynes, and Philippe Bourdeau. Embankment Widening Design Guidelines and Construction Procedures. West Lafayette, IN: Purdue University, 1999. http://dx.doi.org/10.5703/1288284313202.

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