Relevant bibliographies by topics / Unducted and ducted turbomachinery

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

Academic literature on the topic 'Unducted and ducted turbomachinery'

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

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Journal articles on the topic "Unducted and ducted turbomachinery"

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Денисюк, Олеся Валеріївна. "Оцінка характеристик закапотованого гвинтовентилятора ТРДД з надвисоким сту-пенем двоконтурності". Aerospace technic and technology, № 4sup1 (27 серпня 2021): 41–46. http://dx.doi.org/10.32620/aktt.2021.4sup1.06.

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In many respects, the efficiency and economy of the aircraft are determined by the parameters and characteristics of the power plant. The analysis of trends in the world engine building shows that an increase in the bypass ratio can significantly increase the efficiency of engines. One of the possible technical solutions to ensure the high performance of the perspective engines with an ultra-high bypass ratio is the use of a ducted propeller or propfan. This solution allows you to reduce acoustic radiation. In addition, the main advantage of the ducted propfans is a certain increase in thrust for the same consumed power. When flowing around a ducted propfan, a significant suction force arises on the nose of the profiled ring, the projection of which on the direction of movement provides a positive thrust of the ring. The presence of a duct also leads to a decrease in the final loss of the propeller, which, in turn, leads to an increase in the efficiency of the engine. Ducted and unducted propfans with the same blade row are investigated to assess the characteristics of a ducted propfan. The researches were carried out by the method of numerical experiment. The object of the research is a propfan with an inlet diameter of 2.924 m and the number of blades of 14 for a turbofan engine with a bypass ratio of m = 30. To research the propfan characteristics, a cruising mode of operation was selected in the range of revolutions n = 1500 ... 1650 rpm. with Mach numbers at the input from M = 0.54 to M = 0.8. In this work, the calculation did not take into account the resistance force of the duct. For a qualitative assessment of the flow in the propfan, visualization of the flow lines in the ducted and unducted propfan was obtained. The analysis of the research results showed that for all modes of operation the ducted propfan has a thrust force higher than the unducted propfan. The increase in thrust load reaches 71 ... 76 %. Visualization of the flow lines when flowing around a ducted and unducted propfan showed that the presence of a duct improves the internal aerodynamics of the propfan.
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Smith, L. H. "Unducted Fan Aerodynamic Design." Journal of Turbomachinery 109, no. 3 (1987): 313–24. http://dx.doi.org/10.1115/1.3262108.

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A method being used to design unducted fans, which are counterrotating propellers with unusually high disk loadings, is described. The quasi-three-dimensional approach employed is similar to that used for ducted fan designs; it consists of a circumferential-average flowfield analysis followed by cascade designs that include secondary flow and sweep effects. The open-tip condition enters as a significant secondary flow contribution. Blade shapes defined by this process are analyzed by a three-dimensional Euler solver and final adjustments are made as necessary. Examples of application of the method are presented to elucidate the magnitudes of the phenomena involved.
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Chatterjee, Prasun, and Raymond N. Laoulache. "Performance Modeling of Ducted Vertical Axis Turbine Using Computational Fluid Dynamics." Marine Technology Society Journal 47, no. 4 (2013): 36–44. http://dx.doi.org/10.4031/mtsj.47.4.12.

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AbstractVertical axis turbines (VATs) excel over horizontal axis turbines in their independent flow direction. VATs that operate in an enclosure, e.g., a diffuser shroud, are reported to generate more power than unducted VATs. A diffuser-shrouded, high solidity of 36.67%, three-blade VAT with NACA 633-018 airfoil section is modeled in 2-D using the commercial software ANSYS-FLUENT®. Incompressible, unsteady, segregated, implicit, and second order in time and space solver is implemented in association with the Spalart-Allmaras turbulent model with a reasonable computational cost. The computational results are assessed against experimental data for unducted VAT at low tip speed ratios between 1 and 2 for further numerical analysis on diffuser models. Different diffuser designs are investigated using suitable nozzle size, area ratio, length-to-diameter ratio and angles between the diffuser inner surfaces. The numerical model shows that, for a specific diffuser design, the ducted VAT performance coefficient can be augmented by almost 90% over its unducted counterpart.
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Turkdogru, N., and K. K. Ahuja. "Determination of Geometric Farfield for Ducted and Unducted Rotors." International Journal of Aeroacoustics 11, no. 5-6 (2012): 607–27. http://dx.doi.org/10.1260/1475-472x.11.5-6.607.

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Masukume, Peace-Maker, Golden Makaka, and David Tinarwo. "Technoeconomic Analysis of Ducted Wind Turbines and Their Slow Acceptance on the Market." Journal of Renewable Energy 2014 (2014): 1–5. http://dx.doi.org/10.1155/2014/951379.

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The encasing of wind turbines in a duct to enhance performance is not new. A ducted wind turbine produces more power than an unducted wind turbine of the same parameters. A number of approaches in studying the effects of diffusers and other wind concentrating devices have been done and have resulted in a number of prototypes produced but without any commercialization. The aim of this paper is to investigate the failure of commercialization of ducted turbines. A technical and economic analysis of a ducted turbine is also presented. The work shows that traditional economic methods used to evaluate ducted wind turbines are erroneous; they do not account for external effects of power generation and individual and community benefits derived from this technology. Failure to penetrate the market is due to negative publicity as a result of the erroneous evaluation undertaken and lack of appropriate engineering techniques to protect ducted wind energy systems in extreme wind conditions.
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Green, S. I., and S. Z. Duan. "The Ducted Tip—A Hydrofoil Tip Geometry With Superior Cavitation Performance." Journal of Fluids Engineering 117, no. 4 (1995): 665–72. http://dx.doi.org/10.1115/1.2817320.

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A novel hydrofoil design, consisting of a small diameter flow-through duct affixed to the tip, has been studied. The tip vortex cavitation inception index, σi, of this hydrofoil geometry is about a factor of 2 lower than that of a conventional rounded hydrofoil tip. This inception improvement comes with little associated performance penalty. For angles of attack greater than 8 deg the noncavitating lift-drag ratio is actually superior to that of an unducted hydrofoil of equal span, although with lower wing loadings the hydrofoil performance is diminished by application of the ducted tip. The ducted tip is effective at reducing the tip vortex inception index because, in contrast with the rounded tip, for which vorticity in the Trefftz plane is confined to a line, the ducted tip shed vorticity at the trailing edge is distributed over a line and circle. Distributing the vorticity in this fashion causes the trailing vortex to roll up less tightly, and hence have a higher core pressure and lower σi, than a conventional hydrofoil tip. It is also suspected that the interaction at the microscale level between the flow through the duct, and the flow around it, makes the vortex core size larger, and therefore σi smaller. The ducted tip design has many potential marine applications, including to ship and submarine propellers, submarine control fins, and ship rudders.
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Chapman, C. J. "Sound radiation from a cylindrical duct. Part 2. Source modelling, nil-shielding directions, and the open-to-ducted transfer function." Journal of Fluid Mechanics 313 (April 25, 1996): 367–80. http://dx.doi.org/10.1017/s0022112096002248.

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This paper analyses the sound radiated from the front face of a hard-walled circular cylindrical duct in a subsonic mean flow when the duct contains acoustic sources typical of those in a ducted-fan aeroengine. Two main results are established for modes of any given frequency and circumferential order. The first result is that in certain easily calculated directions, called here the nil-shielding directions, the sound radiated by ducted sources is the same as the sound radiated by the corresponding open sources, i.e. by unducted sources of the same distribution and strength radiating into free space. Thus in these special directions the duct has no noise-shielding effect. The second result is that, in the Kirchhoff approximation, the sound radiated by the open sources in the nil-shielding directions determines the sound radiated by the ducted sources in all directions; i.e. the sound fields radiated by open and ducted sources are related by an open-to-ducted transfer function. This function is such that the sound radiated by the ducted sources is a linear combination of certain diffraction functions, in which the coefficients are given by the sound radiated by the open sources in the nil-shielding directions. The diffraction functions do not depend on the sources and are here calculated explicitly in terms of Bessel functions. The method used in the paper is Kirchhoff's approximation; within linear theory this gives the nil-shielding directions exactly, i.e. in agreement with the Wiener—Hopf solution, and gives the main beam of the radiated field, including the major side-lobes, to good accuracy. The results are relevant to the sound radiated into the forward arc by a ducted turbofan aeroengine.
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Zhang, Tao, and George N. Barakos. "High-Fidelity CFD Validation and Assessment of Ducted Propellers for Aircraft Propulsion." Journal of the American Helicopter Society 66, no. 1 (2021): 1–28. http://dx.doi.org/10.4050/jahs.66.012008.

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This paper presents validation and assessment of ducted propellers for aircraft propulsion. Numerical methods and simulation strategies are put forward, including steady/unsteady high-fidelity computational fluid dynamics (CFD) simulations and simpler momentum-based methods. The validation and comparisons of the methods are made using a ducted propeller proposed by NASA. Simulations are also performed and analyzed at extended advance ratios, blade pitch setting, and cross-wind angles. Comparisons are also made with open propeller counterparts. The ducted propeller shows superior performance over its unducted counterpart in hover and at low advance ratios. The major thrust gain is identified from the combination of duct leading-edge suction and the higher pressure at the diffuser exit. The propeller is off-loaded due to the higher inflow velocities. The ducted propeller is also shown to have less intrusive wake features at low axial speeds. However, as the advance ratio increases, the duct thrust contribution becomes negative and the ducted propeller becomes deficient, due to growing high-pressure areas at the leading edge. At cross-wind, high-fidelity CFD simulations offer accurate aerodynamic loads predictions despite the complex flow features. The duct surface separation is found to be delayed due to the propeller suction, while the propeller is shown shielded by the duct, thereby suffering less from the unbalanced inflow velocities. Decomposition of induced velocities by each part is carried out and presented. A large, nonlinear extra induction component, due to mutual interactions of the duct and the propeller, is observed and found favorable for the performance augmentation.
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d’Auria, Fabrizio, Luca d’Agostino, and Christopher E. Brennen. "Dynamic Response of Ducted Bubbly Flows to Turbomachinery-Induced Perturbations." Journal of Fluids Engineering 118, no. 3 (1996): 595–601. http://dx.doi.org/10.1115/1.2817800.

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The present work investigates the dynamics of the three-dimensional, unsteady flow of a bubbly mixture in a cylindrical duct subject to a periodic pressure excitation at one end. One of the purposes is to investigate the bubbly or cavitating flow at inlet to or discharge from a pump whose blade motions would provide such excitation. The flow displays various regimes with radically different wave propagation characteristics. The dynamics effects due to the bubble response may radically alter the fluid behavior depending on the void fraction of the bubbly mixture, the mean bubble size, the pipe diameter, the angular speed of the turbomachine and the mean flow Mach number. This simple linearized analysis illustrates the importance of the complex interactions of the dynamics of the bubbles with the average flow, and provides information on the propagation and growth of the turbopump-induced disturbances in the feed lines operating with bubbly or cavitating liquids. Examples are presented to illustrate the influence of the relevant flow parameters. Finally, the limitations of the theory are outlined.
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Chang, J. Y., C. W. Yu, and R. L. Webb. "Identification of Minimum Air Flow Design for a Desktop Computer Using CFD Modeling." Journal of Electronic Packaging 123, no. 3 (2000): 225–31. http://dx.doi.org/10.1115/1.1348012.

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This paper reports the results of CFD analysis to cool the 30-W socketed CPU of a desktop computer with minimum air flow rate and minimum heat sink size. This was achieved using only the fan in the power supply for all air movement in the chassis. A duct was employed to direct the air flow over the CPU and then to the inlet air vents of the power supply. Use of this duct allowed more than 10°C reduction of the CPU case temperature, relative to an unducted design. The CFD analysis results were confirmed by experiment, and the predicted CPU case temperatures agreed within ±2.9°C of the experimental values for the ducted cases. This paper describes the methodology of CFD analysis for the heat sink/duct design, and describes experimental procedures to validate the predictions.
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Dissertations / Theses on the topic "Unducted and ducted turbomachinery"

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Siddappaji, Kiran. "On the Entropy Rise in General Unducted Rotors using Momentum, Vorticity and Energy Transport." University of Cincinnati / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1535464679934565.

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Buttgereit, Ruediger Volker. "The fluid dynamic study of ducted and unducted Wells turbines in undirectional and oscillatory flows." Thesis, Imperial College London, 1998. http://hdl.handle.net/10044/1/8885.

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Roddis, Mark Edward. "On the inverse design of marine ducted propulsor blading." Thesis, University College London (University of London), 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.265865.

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Book chapters on the topic "Unducted and ducted turbomachinery"

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Lewis, R. I. "Ducted propellers and fans." In Turbomachinery Performance Analysis. Elsevier, 1996. http://dx.doi.org/10.1016/b978-034063191-1/50009-x.

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Dixon, S. L., and C. A. Hall. "Axial-Flow Compressors and Ducted Fans." In Fluid Mechanics and Thermodynamics of Turbomachinery. Elsevier, 2010. http://dx.doi.org/10.1016/b978-1-85617-793-1.00005-5.

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Dixon, S. L., and C. A. Hall. "Axial-Flow Compressors and Ducted Fans." In Fluid Mechanics and Thermodynamics of Turbomachinery. Elsevier, 2014. http://dx.doi.org/10.1016/b978-0-12-415954-9.00005-x.

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Conference papers on the topic "Unducted and ducted turbomachinery"

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Hall, Edward J., and Robert A. Delaney. "Time-Dependent Aerodynamic Analysis of Ducted and Unducted Propfans at Angle of Attack." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-190.

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A three-dimensional unsteady aerodynamic analysis is described for predicting the time-dependent flow about ducted and unducted propfans operating at angle of attack. Although the freestream is assumed to be uniform, the flow relative to the rotating blades varies with circumferential position, resulting in an inherent unsteadiness due to the nonaxial inflow. The time-dependent Euler equations are solved utilizing a Runge-Kutta time-stepping scheme. The analysis is based on a finite-volume discretization employing a multiple-block grid network. To permit the use of large calculation time steps, an implicit residual smoothing scheme previously tested for unsteady flow calculations in two dimensions is extended to three spatial dimensions. For unducted propfans, a single H-type grid block is used for each blade passage to determine the time-periodic flowfield. For ducted propfans (ultra-high bypass fans) a body-centered C-type grid is wrapped about the cowl to improve the accuracy of the analysis in the high gradient flow region near the cowl leading edge. Numerical results are compared with available data for both ducted and unducted propfans operating at angle of attack.
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Brailko, I. A., V. I. Mileshin, M. A. Nyukhtikov, and S. V. Pankov. "Computational and Experimental Investigation of Unsteady and Acoustic Characteristics of Counter-Rotating Fans." In ASME 2004 Heat Transfer/Fluids Engineering Summer Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/ht-fed2004-56435.

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The matter of developing counter-rotating fans for advanced next generation aeroengines with ducted and unducted propfans is very important [1]. Counter-rotating fans can be made with fixed blades. This article considers tractor propfans consisting of two counter-rotating rotors of variable pitch (VPR) which valuable property is the possibility to turn their blades about the radial axis in order they can take the optimal position in direct thrust regimes, and to obtain a reverse thrust when turning them by a rather large angle. In this case there is no necessity to use a bulky special clamshell-type thrust reverser. In the 1-st phase of designing new CRFs it is necessary, by calculation or experimentally, to show the possibility of obtaining gasdynamic effectiveness of such fans up to the level of single-rotor fans or, at least, to obtain η*ad.f ≥ 0.90÷0.91. But the main thing is to substantiate the feasibility of getting high acoustic characteristics. CIAM (Central Institute of Aviation Motors) is carrying out calculation-experimental investigations of the SV-92 ducted counter-rotating propfan (DCRP) model (the SV-92 is an advanced fan for ultra-high bypass ratio engine [2]) as well as the SV-27 CRF (Fig. 1, Table 1) with unducted rotors for the test aircraft. This paper presents some results on gasdynamic and acoustic characteristics for the SV-27 CRF only. These investigations are aimed at providing the meeting of the test aircraft perceivable noise to ICAO chapter IV regulations.
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Rife, M. E., F. Barbarossa, A. B. Parry, J. S. Green, and L. di Mare. "Minimisation of Ducted Flow Non-Uniformity Caused by Downstream Blockages." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56199.

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Flow in annular ducts is sensitive to the presence of downstream blockages which can cause flow non-uniformities propagating far upstream of the blocking body. These effects can be exacerbated in swirling flows where a cascade of uniform guide vanes is present upstream of the blockage. This work uses two- and three-dimensional boundary singularity methods to model and optimise a guide vane cascade geometry to minimise the upstream velocity distortion. Starting from a uniform cascade, the geometry is modified to provide a uniform upstream velocity distribution and minimised blade-to-blade loading in two dimensions. The new geometry is then extrapolated to a three-dimensional annulus. A three-dimensional tool is used to further modify the geometry in three dimensions to minimise the velocity distortion in the whole annulus upstream of the cascade.
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Sen, Uddalok, Tryambak Gangopadhyay, Chandrachur Bhattacharya, et al. "Investigation of Ducted Inverse Nonpremixed Flame Using Dynamic Systems Approach." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-58179.

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Gas turbine combustion has a number of practical applications, including aviation engines, ocean vessels, and tanks. The various advantages of normal diffusion flames, such as increased flame stability and reduced susceptibility to dynamic instabilities, has made it the de facto industrial standard. However, high NOx emission and sooting from such flames is a major problem, particularly for heavier hydrocarbons fuels. In that regard, the inverse diffusion flame offers a feasible alternative; but the dynamic response of such a flame, particularly in ducted conditions — where the unsteady heat release interacts with the duct acoustics — is relatively less researched. In the present work, an experimental investigation of a laboratory-scale inverse diffusion flame has been carried out. The inverse diffusion flame is found in applications like rocket motors, gas turbine combustors, and furnaces. In the present study, inverse diffusion flame from a coaxial burner inside a quartz tube was studied. The position of the duct with respect to the flame was kept fixed, while the global equivalence ratio was varied by keeping the air flow rate constant and changing the fuel flow rate. Various tools of nonlinear dynamics such as phase space reconstruction and recurrence quantification have also been used for dynamic characterization of such flames. The results show that the dynamics of the flame strongly depends on the global equivalence ratio.
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Rivarolo, Massimo, Alessandro Spoladore, Carlo Cravero, et al. "Design and Test Campaign of a Ducted Horizontal Axis Wind Turbine." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75029.

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Electrical energy production by wind energy has assumed more and more relevance in the last years. This paper presents the design of a ducted horizontal axis wind turbine, in order to enhance the performance. The study compares the energy production of a ducted turbine to a traditional free turbine, highlighting the different features. In the first part of the work, different possible geometries have been investigated through a quasi-1D model, using correlations from literature to evaluate pressure, velocity and producible electrical power by the wind turbine. A 3D CFD model, in a set of configurations, has confirmed the preliminary results. The most promising geometries have been selected by combining the outputs of the two models. In order to confirm the results obtained by the numerical models, a test rig has been assembled at the wind tunnel of the Polytechnic School of the University of Genoa. Different possible configurations of the wind energy harvesting system have been tested: free turbine, horizontal duct, convergent duct and convergent-divergent ducts (with the turbine installed in the throat section). In particular, the convergent-divergent duct has shown the best results, with an increase factor close to 2.5 in terms of produced power, compared to the reference free turbine. Finally, the results obtained in the experimental campaign have been used to validate the two models (1D and 3D CFD). Considering the advantages in terms of energy production, this kind of configuration can be considered an interesting solution for many different situations, including energy harvesting.
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Zawislak, Maverick, and Michael Birk. "Experimental Drag and Mixing From Lobed Nozzles Under High Swirl Conditions From a Ducted Fan." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15211.

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Abstract The availability of aerodynamic performance and vorticity production data from mixers under swirl was a challenge for future full-scale design and CFD validation. This paper presents an experimental comparison of drag and mixing performance of a circular trialing edge, lobed nozzle and scalloped nozzle under high swirl conditions as produced by a ducted fan in a subsonic wind tunnel. The design methodology is shared in detail allowing for geometry reproduction. Swirl angles produced by the fan naturally varied between 12° up to 45° according to a free-vortex profile. Performance is compared in terms of net thrust, uniformity factor and vorticity production as measured by 6-component loadcells and a seven-hole pressure probe traverse. The goal of this work was threefold: to study the axial and normal vorticity production from mixers produced by the design methodology, a preliminary investigation into lobed mixers potential in engine plume cooling and to provide a data set for RANS-CFD validation. A better understanding of lobed mixer mixing mechanisms relative to performance is offered. It is shown that the change in minimum throttle to achieve forward thrust varied between devices as did the twist load due to angular forces. A 4% reduction in required fan power to achieve forward thrust was achieved with the lobed mixer. Furthermore, maximum net thrust increased up to 20% with the mixing nozzles compared to the standard round nozzle suggesting flow straightening can lead to thrust gain in high swirling jet flows to a level that counters increases in drag. Axial and normal vorticity were clearly identified. Co-rotating vortex pairs were produced by the mixers of physical size proportional to the lobe height and wavelength. Axial vorticity levels integrated up to 110% of the round nozzle and occupied 5 times the area. Similarly, integrated normal vorticity increased up to 80% over an area 120% larger. Uniformity factor was best for the scalloped mixer due to enhanced mass flow entrainment through the notch and not the vortex production itself.
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Nyukhtikov, Mikhail A., Anton A. Rossikhin, Vasily V. Sgadlev, and Igor A. Brailko. "Numerical Method for Turbomachinery Tonal Noise Generation and Radiation Simulation Using CAA Approach." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51182.

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The numerical method for 3D calculation of the turbomachinery tonal noise generation, propagation and radiation in the near and far fields taking account of the rotor-stator interaction is developed in CIAM. The method is based on the direct numerical solution of three-dimensional Euler equations for disturbances in time or in frequency domain using numerical methods of computational acoustics (CAA). For far-field radiation calculation the Ffowcs Williams method is used. The method is build into CIAM domestic aeroacoustic solver 3DAS (3 Dimensional Acoustics Solver). In this paper we present some examples of our method applications for calculation of rotor-stator interaction and propagation: • Ducted fan tonal noise simulation; • Ducted counter-rotated fan noise simulation; • Low pressure turbine tonal noise simulation.
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Bothe, Franziska, Christian Friebe, Martin Heinrich, and Rüdiger Schwarze. "CFD Simulation of Incompressible Turbomachinery — A Comparison of Results From ANSYS Fluent and OpenFOAM." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26338.

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A numerical investigation of incompressible turbomachinery and the comparison of two CFD packages are presented within this paper. A ducted single rotor fan is simulated with OpenFOAM and ANSYS FLUENT by applying methods as comparable as possible. The characteristic maps and flow fields are analyzed and the results from the CFD codes are compared to examine differences regarding accuracy and efficiency. Additionally the influence of the turbulence model is determined. It is found that the CFD programs show a good agreement especially at the machines design point. The information about the flow field of this fan is used for the modelling of a high-performance and energy-efficient ducted contra-rotating fan (CRF). Comparing the CRF simulation results to those of the single rotor fan, a doubling of the total pressure rise and a significant reduction of the swirl in the wake flow can be noticed.
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Risnyk, Sergiy, Andriy Artushenko, Igor Kravchenko, and Sergii Borys. "Experimental Investigation of Two Competitive High Pressure Turbine Blade Cooling Systems." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64915.

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Aeroengine high-pressure turbine (HPT) is the key engine component. HPT blade must withstand high inlet temperatures and mechanical loads providing the necessary level of the efficiency. To achieve these objectives effective and complex blade cooling systems (internal convective and film cooling) are used in the HPT design. The objective of this project is to design and investigate the aeroengine HPT blade cooling system that is able to withstand the blade inlet gas temperature level of approx. 1900K but with the minimal cooling airflow amount. HPT blade of the aeroengine with unducted fan (UDF) was taken as a baseline design, namely, the monocrystal blade with a convective multipass system and the film cooling. Advanced HPT blade inter-wall cooling system was designed, investigated and compared with the typical baseline HPT blade. In the advanced HPT blade inter-wall cooling system special types and structure of cooling channels are used. Both types of cooling systems were investigated experimentally in the turbine rotor of the high temperature core engine. Measurements of turbine blades temperatures were performed using crystal temperature sensors (CTS). HPT blades with two competitive cooling systems incorporated with CTS (0,2–0,3 mm size) were installed in the turbine rotor of the core engine and tested on the engine Maximal rate. After tests and the engine disassembly CTSs were extracted and the characteristics of the CTS crystal lattice were transcribed in temperature values. Thermal state of both two competitive cooling systems was validated by experimental data. Numerical and experimental results obtained in the research of HPT blade cooling system are presented in the article. Aeroengine high pressure turbine blade cooling systems designs are described.
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Yu, Wenjun, Huanxian Bu, and Xun Huang. "Beamforming and Compressive Sensing Mode Detection of Duct Acoustic Source by Sensor Array." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75260.

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Low noise design and testing methods for aeroengine are indispensable for civil aviation industry with the public environmental convern growing and the stringent regulations established. A novel array testing approach is proposed to reconstruct spinning modal fan noise amplitude from scattered sound wave measurements outside the jet flow downstream to an unflanged duct. The proposed approach relies on the forward propagation model based on the Wiener-Hopf method. The key contribution of this work is the development of the inverse acoustic scattering methods using a non-classical beamforming and a compressive sensing strategies. The performance of the proposed strategies are demonstrated with various numerical simulations, which show that the deconvolution method is more generic while the compressive sensing method is more efficient. The reconstruction results from both methods are comparable in terms of accuracy and dynamic range. Overall, the proposed testing approach should be able to extend the current duct acoustic array testing capability and help the design and evaluation of low-noise ducted fan system.
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