Relevant bibliographies by topics / Turbomachinery flow

Academic literature on the topic 'Turbomachinery flow'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Turbomachinery flow"

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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. "Simulation of Hybrid Mesh Turbomachinery using CFD and Additive Technologies." Civil Engineering Journal 8, no. 12 (December 1, 2022): 3815–30. http://dx.doi.org/10.28991/cej-2022-08-12-011.

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This paper develops schematics and evaluates the performance of hybrid mesh turbomachinery at the patenting stage of individual technical solutions. This type of turbomachine uses reduced-sized blades and also forms flow channels with a mesh structure between the blades. The research methods are based on simulations using computational fluid dynamics (CFD) and additive technologies. An intermediate conclusion is that a new scientific direction for investigating and creating hybrid mesh turbomachinery equipped with mesh jet control systems was formed to develop Euler's ideas. This paper describes new possibilities for the simultaneous implementation of two workflows in a single impeller: 1) Turbine workflow, and 2) Compressor workflow. Calculation methods showed possible improvements in the performance of the new turbomachines. This paper considers options for mesh turbomachine operation in the two-stage gas generator mode with partial involvement of atmospheric air in the workflow. Preliminary calculations based on examples show that it is possible to expect a two- to four-times increase in thrust when using hybrid mesh turbomachines. Ongoing studies mainly focus on developing multi-mode turbomachinery that works in complicated conditions, such as offshore oil and gas fields, but some research results are applicable in other industries, for example, in developing hybrid propulsion systems or propulsors. Doi: 10.28991/CEJ-2022-08-12-011 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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Bogdanovic-Jovanovic, Jasmina, Bozidar Bogdanovic, and Dragica Milenkovic. "Determination of averaged axisymmetric flow surfaces according to results obtained by numerical simulation of flow in turbomachinery." Thermal Science 16, suppl. 2 (2012): 577–91. http://dx.doi.org/10.2298/tsci120426193b.

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In the increasing need for energy saving worldwide, the designing process of turbomachinery, as an essential part of thermal and hydroenergy systems, goes in the direction of enlarging efficiency. Therefore, the optimization of turbomachinery designing strongly affects the energy efficiency of the entire system. In the designing process of turbomachinery blade profiling, the model of axisymmetric fluid flows is commonly used in technical practice, even though this model suits only the profile cascades with infinite number of infinitely thin blades. The actual flow in turbomachinery profile cascades is not axisymmetric, and it can be fictively derived into the axisymmetric flow by averaging flow parameters in the blade passages according to the circular coordinate. Using numerical simulations of flow in turbomachinery runners, its operating parameters can be preliminarily determined. Furthermore, using the numerically obtained flow parameters in the blade passages, averaged axisymmetric flow surfaces in blade profile cascades can also be determined. The method of determination of averaged flow parameters and averaged meridian streamlines is presented in this paper, using the integral continuity equation for averaged flow parameters. With thus obtained results, every designer can be able to compare the obtained averaged flow surfaces with axisymmetric flow surfaces, as well as the specific work of elementary stages, which are used in the procedure of blade designing. Numerical simulations of flow in an exemplary axial flow pump, used as a part of the thermal power plant cooling system, were performed using Ansys CFX.
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FUNAZAKI, Ken-ichi. "Unsteady Flow Phenomena in Turbomachinery." Proceedings of Mechanical Engineering Congress, Japan 2020 (2020): K05200. http://dx.doi.org/10.1299/jsmemecj.2020.k05200.

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Nishi, Michihiro, Shimpei Mizuki, and Hiroshi Tsukamoto. "Unsteday Flow Phenomena in Turbomachinery." Transactions of the Japan Society of Mechanical Engineers Series B 61, no. 591 (1995): 3811–16. http://dx.doi.org/10.1299/kikaib.61.3811.

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Schröder, Tilman Raphael, Hans-Josef Dohmen, Dieter Brillert, and Friedrich-Karl Benra. "Impact of Leakage Inlet Swirl Angle in a Rotor–Stator Cavity on Flow Pattern, Radial Pressure Distribution and Frictional Torque in a Wide Circumferential Reynolds Number Range." International Journal of Turbomachinery, Propulsion and Power 5, no. 2 (April 17, 2020): 7. http://dx.doi.org/10.3390/ijtpp5020007.

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In the side-chambers of radial turbomachinery, which are rotor–stator cavities, complex flow patterns develop that contribute substantially to axial thrust on the shaft and frictional torque on the rotor. Moreover, leakage flow through the side-chambers may occur in both centripetal and centrifugal directions which significantly influences rotor–stator cavity flow and has to be carefully taken into account in the design process: precise correlations quantifying the effects of rotor–stator cavity flow are needed to design reliable, highly efficient turbomachines. This paper presents an experimental investigation of centripetal leakage flow with and without pre-swirl in rotor–stator cavities through combining the experimental results of two test rigs: a hydraulic test rig covering the Reynolds number range of 4 × 10 5 ≤ R e ≤ 3 × 10 6 and a test rig for gaseous rotor–stator cavity flow operating at 2 × 10 7 ≤ R e ≤ 2 × 10 8 . This covers the operating ranges of hydraulic and thermal turbomachinery. In rotor–stator cavities, the Reynolds number R e is defined as R e = Ω b 2 ν with angular rotor velocity Ω , rotor outer radius b and kinematic viscosity ν . The influence of circumferential Reynolds number, axial gap width and centripetal through-flow on the radial pressure distribution, axial thrust and frictional torque is presented, with the through-flow being characterised by its mass flow rate and swirl angle at the inlet. The results present a comprehensive insight into the flow in rotor–stator cavities with superposed centripetal through-flow and provide an extended database to aid the turbomachinery design process.
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RAHMATI, M. T. "APPLICATION OF A PRESSURE CORRECTION METHOD FOR MODELING INCOMPRESSIBLE FLOW THROUGH TURBOMACHINES." International Journal of Computational Methods 06, no. 03 (September 2009): 399–411. http://dx.doi.org/10.1142/s0219876209001905.

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This article presents the application of a RANS algorithm based on a pressure correction method for incompressible flow simulations of low-speed rotating machines. A numerical scheme is developed by extending a flow analysis in a stationary frame to a rotating frame for turbomachinery applications. The numerical scheme is explained with emphasis on the effect of rotation on the flow fields and turbulence modeling. The results of the numerical calculations for flow through an enclosed turbomachine and an extended turbomachine are compared with the experimental data to judge them on realistic flow patterns. The numerical solutions have shown reasonable agreement with the experimental data which demonstrates the merits and robustness of this numerical scheme.
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Bonalumi, Davide, Antonio Giuffrida, and Federico Sicali. "Thermo-economic analysis of a supercritical CO2-based waste heat recovery system." E3S Web of Conferences 312 (2021): 08022. http://dx.doi.org/10.1051/e3sconf/202131208022.

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This work investigates the performance of a supercritical CO2 cycle as the bottoming cycle of a commercial gas turbine with 4.7 MW of electric power output. In detail, the partial heating cycle is the layout chosen for the interesting trade-off between heat recovery and cycle efficiency with a limited number of components. Single-stage radial turbomachines are selected according to the theory of similitude. In particular, the compressor is a troublesome turbomachine as it works near the critical point where significant variations of the CO2 properties occur. Efficiency values for turbomachinery are not fixed at first glance but result from actual size and running conditions, based on flow rates, enthalpy variations as well as rotational speeds. In addition, a limit is set for the machine Mach numbers in order to avoid heavily loaded turbomachinery. The thermodynamic study of the bottoming cycle is carried out by means of the mass and energy balance equations. A parametric analysis is carried out with particular attention to a number of specific parameters. Considering the power output calculated for the supercritical CO2 cycle, economic calculations are also carried out and the related costs compared to those specific of organic Rankine cycles with similar power output.
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Basson, A., and B. Lakshminarayana. "Numerical Simulation of Tip Clearance Effects in Turbomachinery." Journal of Turbomachinery 117, no. 3 (July 1, 1995): 348–59. http://dx.doi.org/10.1115/1.2835668.

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The numerical formulation developed here includes an efficient grid generation scheme, particularly suited to computational grids for the analysis of turbulent turbo-machinery flows and tip clearance flows, and a semi-implicit, pressure-based computational fluid dynamics scheme that directly includes artificial dissipation, and is applicable to both viscous and inviscid flows. The value of this artificial dissipation is optimized to achieve accuracy and convergency in the solution. The numerical model is used to investigate the structure of tip clearance flows in a turbine nozzle. The structure of leakage flow is captured accurately, including blade-to-blade variation of all three velocity components, pitch and yaw angles, losses and blade static pressures in the tip clearance region. The simulation also includes evaluation of such quantities as leakage mass flow, vortex strength, losses, dominant leakage flow regions, and the spanwise extent affected by the leakage flow. It is demonstrated, through optimization of grid size and artificial dissipation, that the tip clearance flow field can be captured accurately.
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Martelli, F., and V. Michelassi. "Viscous flow calculations in turbomachinery channels." Journal de Physique III 3, no. 2 (February 1993): 237–53. http://dx.doi.org/10.1051/jp3:1993129.

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Dissertations / Theses on the topic "Turbomachinery flow"

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Evers, Ingmar. "Sound generation in turbomachinery flow." Thesis, University of Cambridge, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.624316.

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Ning, Wei. "Computation of unsteady flow in turbomachinery." Thesis, Durham University, 1998. http://etheses.dur.ac.uk/4819/.

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Unsteady flow analysis has been gradually introduced in turbomachinery design systems to improve machine performance and structural integrity. A project on computation of unsteady flows in turbomachinery has been carried out. A quasi 3-D time-linearized Euler/Navier-Stokes method has been developed for unsteady flows induced by the blade oscillation and unsteady incoming wakes, hi this method, the unsteady flow is decomposed into a steady flow plus a harmonically varying unsteady perturbation. The coefficients of the linear perturbation equation are formed from steady flow solutions. A pseudo-time is introduced to make both the steady flow equation and the linear unsteady perturbation equation time-independent. The 4-stage Runge-Kutta time-marching scheme is implemented for the temporal integration and a cell-vertex scheme is used for the spatial discretization. A 1-D/2-D nonreflecting boundary condition is applied to prevent spurious reflections of outgoing waves when solving the perturbation equations. The viscosity in the unsteady Navier- Stokes perturbation equation is frozen to its steady value. The present time-linearized Euler/Navier-Stokes method has been extensively validated against other well- developed linear methods, nonlinear time-marching methods and experimental data. Based upon the time-linearized method, a novel quasi 3-D nonlinear harmonic Euler/Navier-Stokes method has been developed. In this method, the unsteady flow is divided into a time-averaged flow plus an unsteady perturbation. Time-averaging produces extra nonlinear "unsteady stress" terras in the time-averaged equations and these extra terras are evaluated from unsteady perturbations. Unsteady perturbations are obtained by solving a first order harraonic perturbation equation, while the coefficients of the perturbation equation are forraed from time-averaged solutions. A strong coupling procedure is applied to solve the time-averaged equation and the unsteady perturbation equation simultaneously in a pseudo-time domain. An approximate approach is used to linearize the pressure sensors in artificial smoothing
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Pelton, Robert John. "One-Dimensional Radial Flow Turbomachinery Performance Modeling." Diss., CLICK HERE for online access, 2007. http://contentdm.lib.byu.edu/ETD/image/etd2192.pdf.

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Khobeiz, Mohamed Hussien. "Numerical simulation of viscous incompressible turbomachinery flow." Thesis, University of Sheffield, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.338828.

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Kempe, Andreas. "Low coherence interferometry in turbomachinery and flow velocimetry /." Zürich : Laboratory of Fluiddynamics, Swiss Federal Institute of Technology (ETH) Zürich, 2007. http://e-collection.ethbib.ethz.ch/show?type=diss&nr=16962.

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Schulte, Volker Benno. "Unsteady separated boundary layers in axial-flow turbomachinery." Thesis, University of Cambridge, 1995. https://www.repository.cam.ac.uk/handle/1810/252035.

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Wang, Xiao. "A preconditioned algorithm for turbomachinery viscous flow simulation." Diss., Mississippi State : Mississippi State University, 2005. http://sun.library.msstate.edu/ETD-db/ETD-browse/browse.

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Addison, John Stephen. "Wake-boundary layer interaction in axial flow turbomachinery." Thesis, University of Cambridge, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.357704.

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Tiow, Wee Teck. "Inverse design of turbomachinery blades in rotational flow." Thesis, University College London (University of London), 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.325463.

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Birch, N. T. "Turbulence and transition modelling in turbomachinery flows." Thesis, Cranfield University, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.379491.

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Books on the topic "Turbomachinery flow"

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Schobeiri, Meinhard T. Turbomachinery Flow Physics and Dynamic Performance. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-24675-3.

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Schobeiri, Meinhard. Turbomachinery Flow Physics and Dynamic Performance. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/b137854.

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Schobeiri, Meinhard. Turbomachinery flow physics and dynamic performance. 2nd ed. New York: Springer, 2012.

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Schobeiri, Meinhard. Turbomachinery Flow Physics and Dynamic Performance. 2nd ed. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012.

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Turbomachinery flow physics and dynamic performance. Berlin: Springer, 2005.

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Caughey, D. A. Multigrid calculation of three-dimensional turbomachinery flows. Ithaca, New York: Fluid Dynamics and Aerodynamics Program, Sibley School of Mechanical and Aerospace Engineering, Cornell University, 1989.

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Montgomery, Matthew D. A three-dimensional linearized unsteady Euler analysis for turbomachinery blade rows. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.

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Lepicovsky, Jan. Use of pressure sensitive paint for diagnostics in turbomachinery flows with shocks. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2000.

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Chung-hua, Wu. A general theory of two-and three-dimensional rotational flow in subsonic and transonic turbomachines. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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Chung-hua, Wu. A general theory of two-and three-dimensional rotational flow in subsonic and transonic turbomachines. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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Book chapters on the topic "Turbomachinery flow"

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Sultanian, Bijay K. "Compressible Flow." In Fluid Mechanics and Turbomachinery, 67–100. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-4.

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Sultanian, Bijay K., and Bijay K. Sultanian. "Potential Flow." In Fluid Mechanics and Turbomachinery, 101–21. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-5.

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Sultanian, Bijay K. "Boundary Layer Flow." In Fluid Mechanics and Turbomachinery, 155–71. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-7.

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Wiederhold, Olaf, Rudibert King, and Bernd R. Noack. "Robust Control in Turbomachinery Configurations." In Active Flow Control II, 187–201. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-11735-0_13.

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Schobeiri, Meinhard T. "Introduction, Turbomachinery, Applications, Types." In Turbomachinery Flow Physics and Dynamic Performance, 3–14. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-24675-3_1.

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Schobeiri, Meinhard T. "Differential Balances in Turbomachinery." In Turbomachinery Flow Physics and Dynamic Performance, 29–57. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-24675-3_3.

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Schobeiri, Meinhard T. "Integral Balances in Turbomachinery." In Turbomachinery Flow Physics and Dynamic Performance, 59–122. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-24675-3_4.

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Schobeiri, Meinhard T. "Theory of Turbomachinery Stages." In Turbomachinery Flow Physics and Dynamic Performance, 123–44. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-24675-3_5.

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Schobeiri, Meinhard. "Introduction, Turbomachinery, Applications, Types." In Turbomachinery Flow Physics and Dynamic Performance, 1–12. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-26591-7_1.

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Schobeiri, Meinhard. "Differential Balances in Turbomachinery." In Turbomachinery Flow Physics and Dynamic Performance, 27–67. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-26591-7_3.

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Conference papers on the topic "Turbomachinery flow"

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MATUS, RICHARD, and RICHARD LOUNSBURY. "An unstructured grid flow solver for turbomachinery flows." In 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1913.

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Dring, Robert P., and H. David Joslyn. "Through-Flow Modeling of Axial Turbomachinery." In ASME 1985 Beijing International Gas Turbine Symposium and Exposition. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-igt-42.

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Through-flow analysis, which is at the heart of the aerodynamic design of turbomachinery, requires as aerodynamic input a row-by-row description of the airfoil loss, deviation, and blockage. Loss and deviation have been investigated extensively in both cascades and rotating rigs as well as in numerous two- and three-dimensional analytical studies. Blockage, however, has received far less attention. As defined herein, blockage is a measure of the departure of the flow field from the condition of axisymmetry which is assumed in the through-flow analysis. The fullspan blockage distributions calculated from measured single-stage rotor wake data were used to provide the input to the through-flow analysis, along with the measured fullspan distributions of loss and deviation. Measured and computed results are compared for the single-stage rotor operating with both thick and thin inlet hub and tip boundary layers. It is demonstrated that both the level and the spanwise and streamwise distributions of blockage have a strong impact on the computed rotor exit flow field.
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Martelli, Francesco, and Vittorio Michelassi. "Viscous Flow Calculations in Turbomachinery Channels." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-5.

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An implicit procedure based on the artificial compressibility formulation is presented for the numerical solution of the two-dimensional incompressible steady Navier-Stokes equations in the presence of large separated regions. Turbulence effects are accounted for by the Chien low Reynolds number form of the K-ε turbulence model and the Baldwin-Lomax algebraic expression for turbulent viscosity. The governing equations are written in conservative form and implicitly solved in fully coupled form using the approximate factorization technique. Preliminary tests were carried out in a laminar flow regime to check the accuracy and stability of the method in two-dimensional and cylindrical axisymmetric flow configurations. After testing in laminar and turbulent flow regimes and comparing the two turbulence models, the code was successfully applied to an actual gas turbine diffuser at low Mach numbers.
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Steinthorsson, Erlendur, Ali Ameri, David Rigby, Erlendur Steinthorsson, Ali Ameri, and David Rigby. "TRAF3D.MM - A multi-block flow solver for turbomachinery flows." In 35th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-996.

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Schulz, Jan, Melanie Fuchs, Wolfgang Neise, and Michael Möser. "Active Flow Control to Reduce the Tonal Noise Components of Axial Turbomachinery." In 1st Flow Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2949.

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Doukelis, A., and K. Mathioudakis. "Turbomachinery Flow Measurements Using Long-Nose Probes." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38488.

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The present work provides a detailed account of a pneumatic measuring technique appropriate for flow field measurements in turbomachinery configurations, making use of long-nose 5-hole probes. The way of obtaining flow quantities in a frame of reference on the sensing head of the probe is first addressed. Transformation of velocity co-ordinates from the probe frame to a stationary frame, customary for turbomachinery flows, is then discussed. Sources of error are also discussed, with particular attention on those that can be introduced by the nose geometry and the co-ordinate transformations. The potential of the measuring technique is demonstrated by presenting the application of the technique for measurements in an annular cascade facility. The results are compared to results obtained by a 3-D Laser-Doppler Anemometer.
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Sheffer, S., and K. Rao. "Nonreflecting boundary conditions for turbomachinery flow calculations." In 30th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-3203.

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Dring, Robert P., and Gordon C. Oates. "Through Flow Theory for Nonaxisymmetric Turbomachinery Flow: Part I — Formulation." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-304.

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Through flow theory has been limited in its applicability and in its accuracy by the fact that it has not historically been cast in a form which can account for the nonaxisymmetries that naturally arise in turbomachinery flow due to the presence of finite numbers of rotor and stator airfoils. The attempt to circumvent this limitation by the introduction of an aerodynamic blockage factor has been demonstrated in earlier work to produce fundamental inconsistencies in the calculation which lead to significant errors in the regions of the flow where the nonaxisymmetries are severe. The formulation in Part I of the present work is a derivation of a system of through flow equations for nonaxisymmetric flow. A benchmark data base is used in Part II to provide input to the calculation and to help identify the dominant terms. It is demonstrated that the dominant effect of nonaxisymmetry is contained in two terms that relate the total pressure of the averaged flow to the mass averaged total pressure. It is also demonstrated that the present formulation produces a result which is more accurate than that obtained with the historical blockage-based formulation.
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Dring, Robert P., and Gordon C. Oates. "Through Flow Theory for Nonaxisymmetric Turbomachinery Flow: Part II — Assessment." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-305.

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Through flow theory has been limited in its applicability and in its accuracy by the fact that it has not historically been cast in a form which can account for the nonaxisymmetries that naturally arise in turbomachinery flow due to the presence of finite numbers of rotor and stator airfoils. The attempt to circumvent this limitation by the introduction of an aerodynamic blockage factor has been demonstrated in earlier work to produce fundamental inconsistencies in the calculation which lead to significant errors in the regions of the flow where the nonaxisymmetries are severe. The formulation in Part I of the present work is a derivation of a system of through flow equations for nonaxisymmetric flow. A benchmark data base is used in Part II to provide input to the calculation and to help identify the dominant terms. It is demonstrated that the dominant effect of nonaxisymmetry is contained in two terms that relate the total pressure of the averaged flow to the mass averaged total pressure. It is also demonstrated that the present formulation produces a result which is more accurate than that obtained with the historical blockage-based formulation.
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10

Bettrich, Valentin, and Reinhard Niehuis. "Experimental Investigation of Geometric Design Parameters of a High Frequency Fluidic Oscillator at Turbomachinery Relevant Conditions." In 2018 Flow Control Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3059.

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Reports on the topic "Turbomachinery flow"

1

Tan, Choon S. Aerospace Turbomachinery Flow Physics. Fort Belvoir, VA: Defense Technical Information Center, August 2003. http://dx.doi.org/10.21236/ada418327.

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2

Govindan, T. R., F. J. De Jong, W. R. Briley, and H. McDonald. Rotating Flow in Radial Turbomachinery. Fort Belvoir, VA: Defense Technical Information Center, May 1990. http://dx.doi.org/10.21236/ada222885.

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3

Greitzer, Edward M., Alan H. Epstein, Michael B. Giles, James E. McCune, and Choon S. Tan. Unsteady Flow Phenomena in Turbomachines. Fort Belvoir, VA: Defense Technical Information Center, January 1990. http://dx.doi.org/10.21236/ada218370.

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4

Tabakoff, W. Study of Particulated Flows and Erosion in Turbomachinery. Fort Belvoir, VA: Defense Technical Information Center, August 1986. http://dx.doi.org/10.21236/ada172965.

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5

Katz, Joseph, and Charles Meneveau. Instrumentation to Support PIV and HPIV Measurements in an Axial Turbomachine Flow Visualization Facility. Fort Belvoir, VA: Defense Technical Information Center, June 2001. http://dx.doi.org/10.21236/ada388848.

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