Готові списки джерел за темами / Blade motion

Добірка наукової літератури з теми "Blade motion"

Автор: Grafiati
Опубліковано: 6 вересня 2023

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Статті в журналах з теми "Blade motion"

1

Thresher, R. W., A. D. Wright, and E. L. Hershberg. "A Computer Analysis of Wind Turbine Blade Dynamic Loads." Journal of Solar Energy Engineering 108, no. 1 (February 1, 1986): 17–25. http://dx.doi.org/10.1115/1.3268046.

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The flapping motion of a single wind turbine rotor blade has been analyzed and equations describing the flapping motion have been developed. The analysis was constrained to allow only flapping motions for a cantilevered blade, and the equations of motion are linearized. A computer code, called FLAP (Force and Loads Analysis Program), to solve the equations of motion and compute the blade loads, has been completed and compared to measured loads for a 3-bladed downwind turbine with stiff blades. The results of the program are presented in tabulated form for equidistant points along the blade and equal azimuth angles around the rotor disk. The blade deflection, slope and velocity, flapwise shear and moment, edgewise shear and moment, blade tension, and blade torsion are given. The deterministic excitations considered in the analysis include wind shear, tower shadow, gravity, and a prescribed yaw motion.
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2

Stanisławski, Jarosław. "Simulation of Boundary States of Helicopter Flight." Journal of KONES 26, no. 2 (June 1, 2019): 137–44. http://dx.doi.org/10.2478/kones-2019-0042.

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Abstract Results of simulation of main rotor blade loads and deformations, which can be generated during boundary states of helicopter flight, are presented. Concerned cases of flight envelope include hover at maximum height, level flight at high velocity, pull-up manoeuvres applying cyclic pitch and mixed collective and cyclic control. The simulation calculations were executed for data of light helicopter with three-bladed articulated rotor. For analysis, the real blades are treated as elastic axes with distributed masses of blade segments. The model of deformable blade allows for out-of-plane bending, in plane bending, and torsion. For assumed flight state of helicopter, the equations of rotor blades motion are solved applying Runge-Kutta method. According to Galerkin method, for each concerned azimuthal position of blade the parameters of its motions are assumed as a combination of considered bending and torsion eigen modes of the blade. The loads of rotor blades generated during flight depend due to velocity of flight, helicopter mass, position of rotor axis in air and deflections of swashplate that correspond to collective and cyclic pitch angle applied to rotor blades. The results of simulations presenting rotor loads and blade deformations are shown in form of time-runs and as plots of rotor-disk distributions. The simulations of helicopter flight states may be useful for prediction the conditions of flight-tests without exceeding safety boundaries or may help to define limitations for manoeuvre and control of helicopter.
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3

Christensen, René H., and Ilmar F. Santos. "Modal Controllability and Observability of Bladed Disks and their Dependency on the Angular Velocity." Journal of Vibration and Control 11, no. 6 (June 2005): 801–28. http://dx.doi.org/10.1177/1077546305054596.

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Rotating bladed disks are characterized by time-variant mathematical models presenting vibration coupling among rotor lateral motion and blade flexible motion. Moreover, they present parametric vibration modes and the blade natural frequencies may change depending on the angular velocity due to centrifugal stiffening. Consequently, the degree of controllability and observability of bladed disks also becomes time-varying, dependent on angular velocity, and a difficult task to analyze. In this paper we present a methodology for analyzing the modal controllability and observability of a bladed disk, based on time-variant modal analysis. The method takes into account time-variant parametric vibration mode shapes, and quantitative measures of modal controllability and observability are calculated. Numerical results show that, in order to control blade and shaft vibrations of a tuned bladed disk, by means of active control, blade-based as well as shaft-based sensing and actuation are required to monitor and control all vibration levels. If rotor blades are properly mistuned, the results show that disk as well as blade vibrations are monitorable and controllable by using only shaft-based sensing and actuation. The analysis shows why the mistuned disk becomes theoretically controllable and observable, via the presence of parametric mode shape components. Finally, the results show that the levels of controllability and observability depend significantly on the angular velocity, no matter the number of applied sensors and actuators used or their positioning.
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4

He, Shangwen, Kunli Si, Bingbing He, Zhaorui Yang, and Ying Wang. "Rub-Impact Dynamics of Shrouded Blades under Bending-Torsion Coupling Vibration." Symmetry 13, no. 6 (June 16, 2021): 1073. http://dx.doi.org/10.3390/sym13061073.

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Shroud devices which are typical cyclic symmetric structures are widely used to reduce the vibration of turbine blades in aero engines. Asymmetric rub-impact of adjacent shrouds or aerodynamic excitation forces can excite the bending-torsion coupling vibration of shrouded blades, which will lead to complex contact motions. The aim of this paper is to study the rub-impact dynamic characteristics of bending-torsion coupling vibration of shrouded blades using a numerical method. The contact-separation transition mechanism under complex motions is studied, the corresponding boundary conditions are set up, and the influence of moments of contact forces and aerodynamic excitation forces on the motion of the blade is considered. A three-degree-of-freedom mass-spring model including two mass blocks with the same size and shape is established to simulate the bending-torsion coupling vibration, and the dynamic equations of shrouded blades under different contact conditions are derived. An algorithm based on the fourth-order Runge–Kutta method is presented for simulations. Variation laws of the forced response characteristics of shrouded blades under different parameters are studied, on the basis of which the method to evaluate the vibration reduction characteristics of the shrouded blade system when the motion of the blade is chaotic is discussed. Then, the vibration reduction law of shrouded blades under bending-torsion coupling vibration is obtained.
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5

Beresnevich, Vitaly, Marina Cerpinska, Janis Viba, and Martins Irbe. "Dynamics analysis and structural synthesis of wind energy production device with closed loop conveyor." Vibroengineering PROCEDIA 44 (August 25, 2022): 156–62. http://dx.doi.org/10.21595/vp.2022.22867.

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This paper deals with a dual design device for wind energy production, in which the movement of the blade consists of several stages, that is, two stages of rotation about two fixed axes and two stages of the blades straight translation movement. The proposed design offers a closed-shaped flattened conveyor equipped with several identical flat-shaped blades. The blades are mounted on a conveyor belt and have an opportunity to move together with the belt in one straight line direction. Therefore, air flow kinetic energy is transformed into translation motion of flat blades. The conveyor system has a built-in energy generator. To analyse blade interaction with air flow, a superposition principle is applied, in which the fast chaotic motion of air particles (Brownian motion) is separated from the slow flow motion with the given average velocity. On the base of such separation, a differential equation of motion for the entire conveyor system with one degree of freedom is obtained. Dynamics of the system due to the action of air flow is simulated with computer program Mathcad. Optimization of system parameters is performed, using a generated power as criterion. In addition, motion control at changeable airflow is optimized by selecting the blade orientation and corresponding adjustment of generator.
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6

Stanislawski, Jaroslaw. "A simulation investigation of helicopter ground resonance phenomenon." Aircraft Engineering and Aerospace Technology 91, no. 3 (March 4, 2019): 484–97. http://dx.doi.org/10.1108/aeat-11-2017-0256.

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Purpose The purpose of this paper is to present a simulation method applied for investigation of helicopter ground resonance phenomenon. Design/methodology/approach The considered physical model of helicopter standing on ground with rotating rotor consists of fuselage and main transmission gear treated as stiff bodies connected by elastic elements. The fuselage is supported on landing gear modeled by spring-damper units. The main rotor blades are treated as set of elastic axes with lumped masses distributed along blade radius. Due to Galerkin method, parameters of blades motion are assumed as a combination of bending and torsion eigen modes. A Runge–Kutta method is applied to solve equations of motions of rotor blades and helicopter fuselage. Findings The presented simulation method may be applied in preliminary stage of helicopter design to avoid ground resonance by proper selection of landing gear units and blade damper characteristics. Practical implications Ground resonance may occur in form of violently increasing mutual oscillations of helicopter fuselage and lead-lag motion of rotor blades. According to changes of stiffness and damping characteristics, simulations show stable behavior or arising oscillations of helicopter. The effects of different blade balance or defect of blade damper are predicted. Originality/value The simulation method may help to determine the envelope of safe operation of helicopter in phase of take-off or landing. The effects of additional disturbances as results of blades pitch control as swashplate deflection are introduced.
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7

LeGrand, Scott A., Bradley J. Hindman, Franklin Dexter, Julie B. Weeks, and Michael M. Todd. "Craniocervical Motion during Direct Laryngoscopy and Orotracheal Intubation with the Macintosh and Miller Blades." Anesthesiology 107, no. 6 (December 1, 2007): 884–91. http://dx.doi.org/10.1097/01.anes.0000291461.62404.46.

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Background Previous studies have characterized segmental craniocervical motion that occurs during direct laryngoscopy and intubation with a Macintosh laryngoscope blade. Comparable studies with the Miller blade have not been performed. The aim of this study was to compare maximal segmental craniocervical motion occurring during direct laryngoscopy and orotracheal intubation with Macintosh and Miller blades. Methods Eleven anesthetized and pharmacologically paralyzed patients underwent two sequential orotracheal intubations, one with a Macintosh blade and another with a Miller in random order. During each intubation, segmental craniocervical motion from the occiput to the fifth cervical vertebra (C5) was recorded using continuous lateral cinefluoroscopy. Single-frame images corresponding to the point of maximal cervical motion for both blade types were compared with a preintubation image. Using image analysis software, angular change in the sagittal plane at each of five intervertebral segments was compared between the Macintosh and Miller blades. Results Extension at occiput-C1 was greater with the Macintosh blade compared with the Miller (12.1 degrees +/- 4.9 degrees vs. 9.5 degrees +/- 3.8 degrees, respectively; mean difference = 2.7 degrees +/- 3.0 degrees; P = 0.012). Total craniocervical extension (occiput-C5) was also greater with the Macintosh blade compared with the Miller (28.1 degrees +/- 9.5 degrees vs. 23.2 degrees +/- 8.4 degrees, respectively; mean difference = 4.8 degrees +/- 4.4 degrees; P = 0.008). Conclusions Compared with the Macintosh, the Miller blade was associated with a statistically significant, but quantitatively small, decrease in cervical extension. This difference is likely too small to be important in routine practice.
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8

Person, M. "The Equations of Motion of n-Bladed Propellers with Arbitrarily Positioned Hinges and Their Application to an Experimental One-Bladed Wind Turbine." Proceedings of the Institution of Mechanical Engineers, Part A: Power and Process Engineering 199, no. 4 (November 1985): 237–44. http://dx.doi.org/10.1243/pime_proc_1985_199_030_02.

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The equations of motion of n-bladed propellers with arbitrarily positioned hinges are derived out of the equations of a one-bladed propeller, by superposition. Different types of propellers are compared for time variances at the equations. An unbalanced start-up and the stability analyses (Floquet) of an experimental one-bladed propeller illustrate the need to consider the interaction of the motions of nacelle or hub and blade.
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9

Stanisławski, Jarosław. "A Comparison of Helicopter Main Rotor Features Due to Stiffness of Rotor Blade-Hub Connection." Transactions on Aerospace Research 2018, no. 1 (March 1, 2018): 119–36. http://dx.doi.org/10.2478/tar-2018-0008.

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Abstract The paper presents results of simulation calculations concerning an influence of stiffness of blade-hub connection on rotor loads and blades deflections in hover, level flight and pull up maneuver. The three versions of rotor are considered with articulated, elastic and stiff connections of blades and hub. The blades with the same distributions of stiffness, mass and the same aerodynamic characteristics are applied for all rotor cases. The rotor loads are calculated applying Runge-Kutta method to solve the equations of motion of deformable blades. According to the Galerkin method, the parameters of blades motion are treated as combination of considered blade bending and torsion eigen modes. The results of calculations indicate for possibility to generate the greater rotor control moments and to improve helicopter maneuverability in the case of applying the non-changed blade of articulated rotor combined with elastic rotor hub.
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10

Gribin, Vladimir, Ilya Gavrilov, Aleksandr Tishchenko, Victor Tishchenko, Vitaliy Popov, Sergey Khomyakov, and Roman Alexeev. "Features of liquid phase movement in the inter-blade channel of nozzle blade cascade." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 5 (September 13, 2017): 452–60. http://dx.doi.org/10.1177/0957650917730947.

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The experimental results of wet steam flow in the blade channel of flat nozzle blade cascade have been considered in the paper. The aim of this work is to study the motion of liquid droplets inside the inter-blade channel. Experimental studies were performed on installation circuit of wet steam. In order to obtain velocity fields of droplets in investigated channel, the laser diagnostics system was used. It carries out the cross-correlation method—particle tracking velocimetry. Numerical simulation of wet steam flow in studied channel was performed. According to the obtained data, the main features of the droplets motion in the blade channel have been revealed. Basic droplets streams and the sources of their appearance have been determined. The process of deposition and breakdown of the droplets on the surface of the blades have been studied. It is shown that reflected region of droplets (“fountain”) is formed around the leading edge. The experimental data were compared with the results of numerical simulation of the droplets motion in the flat nozzle blade cascade.
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Дисертації з теми "Blade motion"

1

Pesce, Matthew M. "Unsteady pressure and vorticity fields in blade-vortex interactions." Thesis, This resource online, 1990. http://scholar.lib.vt.edu/theses/available/etd-03122009-040643/.

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2

Chen, Shin-Juh. "Response of blade-row to upstream vortical disturbance in relative motion." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/47382.

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3

King, Robert L. "Nonlinear dynamics in the modeling of helicopter rotor blade lead/lag motion." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA366866.

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Dissertation (Ph.D. in Aeronautical and Astronautical Engineering) Naval Postgraduate School, June 1999.
"June 1999". Dissertation supervisor(s): E. Roberts Wood. Includes bibliographical references (p. 81). Also available online.
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4

Jonnalagadda, V. R. Prasad. "A derivation of rotor blade equations of motion in forward flight and their solution." Diss., Georgia Institute of Technology, 1985. http://hdl.handle.net/1853/12963.

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5

Lutschinger, Dirk. "Turbulence consideration in wind turbine design and its effect on main shaft motion and blade root strain." Thesis, Curtin University, 2016. http://hdl.handle.net/20.500.11937/911.

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This PhD research investigated the influence of turbulence effects on the vibration behaviour of wind turbines. A small laboratory scale wind turbine test facility was developed with special purpose instrumentation and sensors. Experimental investigations of the vibration behaviour of the turbine demonstrated the complexity of the displacements of the main rotor shaft and the strain at the roots of the rotor blade. This research will assist in the ongoing development of improved failure detection mechanisms.
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6

Ozgur, Cumhur. "Three-dimensional Design And Analysis Of A Compressor Rotor Blade." Master's thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/2/12606389/index.pdf.

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Three-dimensional design and three-dimensional CFD analysis of a compressor rotor stage are performed. The design methodology followed is based on a mean line analysis and a radial equilibrium phase. The radial equilibrium is established at a selected number of radii. NACA 65 series airfoils are selected and stacked according to the experimental data available. The CFD methodology applied is based on a three-dimensional, finite difference, compressible flow Euler solver that includes the source terms belonging to rotational motion. The accuracy of the solver is shown by making use of two different test cases. The CFD solution of the designed geometry predicts the static pressure rises and flow turning angles to a good degree of accuracy.
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7

Hirokawa, Yuusuke. "Evaluation of motion correction effect and image quality with the periodically rotated overlapping parallel lines with enhanced reconstruction (PROPELLER) (BLADE) and parallel imaging acquisition technique in the upper abdomen." Kyoto University, 2009. http://hdl.handle.net/2433/126431.

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8

Kim, Young K. "A numerical solution of implicit nonlinear equations of motion for rotor blades." Diss., Georgia Institute of Technology, 1990. http://hdl.handle.net/1853/12047.

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9

Lim, Choon Peng. "Experimental investigation of vortex shedding in high Reynolds number flow over compressor blades in cascade." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Mar%5FLim.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, March 2003.
Thesis advisor(s): Garth V. Hobson, Raymond P. Shreeve. Includes bibliographical references (p. 81-82). Also available online.
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10

Цьонь, Олег Петрович, та O. P. Tsion. "Удосконалення конструкції дообрізувача гички цукрових буряків активного типу". Thesis, Тернопільський національний технічний університет ім. Івана Пулюя, 2014. http://elartu.tntu.edu.ua/handle/123456789/5432.

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Робота виконана у Тернопільському національному технічному університеті імені Івана Пулюя Міністерства освіти і науки України. Захист відбувся “ 27 ” січня 2015 року о “ 14 ” годині на засіданні спеціалізованої вченої ради Д 58.052.02 в Тернопільському національному технічному університеті імені Івана Пулюя за адресою: 46001, м. Тернопіль, вул. Руська, 56, аудиторія 79.
Удосконалення конструктивної схеми доочисника головок коренеплодів, який забезпечує підвищення показників надійності та якості виконання технологічного процесу, можливо досягти шляхом розроблення гичкозрізуючого пристрою з активним плоским ножем. Перевагою запропонованого конструктивного рішення, порівняно з активним дисковим ножем, є підвищена експлуатаційна надійність, значно менша маса та простота виготовлення.
Дисертацію присвячено питанням підвищення ефективності та надійності технологічного процесу дообрізування залишків гички з головок коренеплодів цукрових буряків на основі обґрунтування конструктивно-технологічних параметрів механізму дообрізувача гички активного типу. Теоретично досліджено: процес взаємодії активного плоского ножа з головками коренеплодів при режимі різання з ковзанням; НДС ножа при приведенні у рух; модель руху дообрізувача гички з активним робочим органом по рядках коренеплодів цукрових буряків; коефіцієнт ковзання в системі “коренеплід – плоский ніж”. Експериментально досліджено залежність сили різання головок цукрових буряків активним плоским ножем від робочої швидкості бурякозбирального агрегату; зворотно-поступальної швидкості ножа та товщини його леза; діаметра коренеплодів. Встановлено корозійний вплив на функціональну здатність конструкційних матеріалів ножів середовища соку цукрових буряків. Застосування запропонованої конструкції дообрізувача активного типу дозволить підвищити ефективність та надійність процесу доочищення головок коренеплодів цукрових буряків від залишків гички.
The thesis is dedicated to the problem of improving the efficiency and reliability of technological topping the residual tops of sugar beet crowns taking into consideration the structural and technological parameters of an active type topper. The following aspects are theoretically researched: interaction of an active flat knife with the root beet crowns in mode of cutting with sliding; tensely deformed status of that knife when moving; model of moving the topper with active working bodies along sugar root beets rows; coefficient of sliding in the system “root – flat knife”. The dependence of sugar beet crowns cutting force by means of active flat knife on the working speed of a beet harvester, as well as on the knife reciprocating speed, knife blade thickness, root diameter, is developed experimentally. The corrosion effect of beet juice on functional capability of knife structural materials is researched. The use of active type topper design will improve the efficiency and reliability of toping the sugar beet crowns.
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Книги з теми "Blade motion"

1

Blade runner. Palermo: L'epos, 2009.

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2

Institute, British Film, ed. Blade runner. London: British Film Institute, 1997.

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3

Blade Runner. 2nd ed. Kent: Crescent Moon Publishing, 2013.

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4

Blade runner reloaded. Milano, Italy: FrancoAngeli, 2017.

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5

Menarini, Roy. Ridley Scott: Blade runner. Torino: Lindau, 2000.

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6

Pitts, J. A. Black blade blues. New York: Tor, 2010.

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7

Pitts, J. A. Black blade blues. New York: Tor, 2010.

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8

Marcel, Štefančič, ed. Blade run[n]er: Solze in dež. Ljubljana: Slovenski gledališki in filmski muzej, 1993.

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9

Silbersack, John, and Caitlin Blasdell, eds. Future Noir: The Making of Blade Runner. New York City, New York, USA: HarperPrism, 1996.

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10

Sievert, Johannes F. Theoretische und filmanalytische Aspekte in Ridley Scotts Blade Runner. Alfeld: Coppi Verlag, 2000.

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Частини книг з теми "Blade motion"

1

Danckwardt, Joachim F. "Zum Medienwechsel bei David Lynch: von „motion pictures“ zu „moving paintings“." In Blade Runner, Matrix und Avatare, 397–405. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-25625-7_27.

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2

Betancourt, Michael. "Allusion of Errors in Blade Runner 2049 (2017)." In Ideologies of the Real in Title Sequences, Motion Graphics and Cinema, 177–205. 1. | New York : Routledge 2020. | Series: Routledge studies in media theory & practice ; 8: Routledge, 2019. http://dx.doi.org/10.4324/9780429244094-9.

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3

Sarrafi, Aral, and Zhu Mao. "Using 2D Phase-Based Motion Estimation and Video Magnification for Binary Damage Identification on a Wind Turbine Blade." In Model Validation and Uncertainty Quantification, Volume 3, 145–51. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-74793-4_19.

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4

Zaitsev, Vladimir, Vladimir Konovalov, Anastasia Konovalova, Maria Fomina, and Victoria Zaitseva. "Determining the Nature of Particle Motion on the Blades of a Horizontal Drum of a Mobile Trailer." In Lecture Notes in Networks and Systems, 1209–17. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-11058-0_123.

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5

"Rotor Blade Flapping Motion: Simple Model." In Fundamentals of Helicopter Dynamics, 120–37. CRC Press, 2014. http://dx.doi.org/10.1201/b17314-9.

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6

Prakash, Punit, Praveen Laws, Nishant Mishra, and Santanu Mitra. "Computational Analysis of Symmetric and Cambered Blade Darrieus Vertical Axis Wind Turbine With Bio-Mimicked Blade Design." In Applications of Nature-Inspired Computing in Renewable Energy Systems, 225–40. IGI Global, 2022. http://dx.doi.org/10.4018/978-1-7998-8561-0.ch011.

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Vertical axis wind turbine suffers from low performance, and the need for improvement is a challenge. This work addresses this problem by using computational fluid dynamics. This chapter aims to analyze and compare symmetric and cambered Darrieus turbine. These analyses are usually carried for straight leading-edge blades, and cambered resembles more the natural shape of the wing of birds and other aquatic mammals, which helps them generate extra lift during movement. Moreover, recent studies suggest better performance was observed for NACA0018 symmetric aerofoil blades, and a similar trend has been observed for NACA2412 cambered aerofoil profiles. Turbine models having symmetric NACA0018 and cambered NACA2412 profiles have been studied. By comparing the symmetric model with cambered blade models, differences in coefficient of torque have been presented. OpenFOAM is used for performing the 2D simulation with dynamicOverset-FvMesh for motion solver with overset mesh method. Meshed geometry was constructed with GMSH codes and the simulation uses overPimpleDyMFoam algorithm as a solver.
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Viba, Janis, Vitaly Beresnevich, and Martins Irbe. "Methods and Devices for Wind Energy Conversion." In Wind Turbines - Advances and Challenges in Design, Manufacture and Operation [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.103120.

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The chapter deals with the analysis and optimization of the operational safety and efficiency of wind energy conversion equipment. The newly proposed method of wind energy conversion involves flat blades or space prisms that perform translation motion due to the interaction with air flow. Air flow interactions with 2D moving prisms (convex, concave) are studied by computer simulation. Optimization of prism shape is made using as criteria maximum of generating force and power. Theoretical results obtained are used in the designing of new devices for energy extraction from airflow. Models of wind energy conversion devices equipped with one vibrating blade are developed (quasi translatory blade’s motion model; model with vibrating blade equipped with crank mechanism). The operation of the system due to the action of air flow is simulated with computer programs. Possibilities to obtain energy with generators of different characteristics, using mechatronic control, have been studied. The effect of wind flow with a constant speed and also with a harmonic or polyharmonic component is considered. Partial parametric optimization of the electromechanical system has been performed. The serviceability and main advantages of the proposed methods and devices are confirmed by experiments with physical models in a wind tunnel.
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KAWAI, Tadao, Masami ITO, Yoko SAWA, and Yasuhiro TAKANO. "Inverse Method of Processing Motion Blur for Vibration Monitoring of Turbine Blade." In Condition Monitoring and Diagnostic Engineering Management, 513–20. Elsevier, 2001. http://dx.doi.org/10.1016/b978-008044036-1/50060-3.

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9

Sun, Fengnan, Yan Zhu, Qiyou Cheng, Siwen Wang, and Longtao Xing. "Simulation and Analysis of Dynamic Characteristics of Tilt Rotor/Wing Coupling System." In Advances in Transdisciplinary Engineering. IOS Press, 2022. http://dx.doi.org/10.3233/atde221044.

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Considering the coupling effects of elastic wing, elastic blade, rigid nacelle and connection points between systems, the mathematical model of the coupling system including wing/nacelle/tilting rotor is established. Based on the eigenvalue method, the overall modal changes of the rotor installed on the wing and the effects of speed and offset on the dynamic characteristics of the system are studied. The results show that the wing joint motion mainly affects the backward and forward modes of rotor flapping. Different rotor rotation speeds cause varying degrees of modal frequencies of wings in different flight modes, especially the wing flapping mode. The nacelle tilt angle causes significant changes in wing waving frequency, and other modes are basically unaffected. The shaft length mainly affects the wing shimmy and torsional mode in vertical flight, and the offset basically does not affect the wing modes in the forward flight stage.
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Kinoshita, T., and H. Kobayashi. "Hydrodynamic load acting on an oar blade and an improvement of rower’s motion and equipments by using rowing velocity prediction program." In Hydrodynamics VI: Theory and Applications, 575–81. Taylor & Francis, 2004. http://dx.doi.org/10.1201/b16815-85.

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Тези доповідей конференцій з теми "Blade motion"

1

Virdi, A. S., Q. Zhang, L. He, H. D. Li, and R. Hunsley. "Aerothermal Performance of Shroudless Turbine Blade Tips With Effects of Relative Casing Motion." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2021.

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Recent work has indicated qualitatively different heat transfer characteristics between a transonic blade tip and a subsonic one. High resolution experimental data can be acquired for blade tip heat transfer research using a high speed linear cascade. While recognising an important role played by the cascade tests in validating computational models at the same conditions, some questions arise in relation to the effects of relative casing motion: 1) Does the relative casing movement change the main flow physics influencing the blade tip aerothermal performance? 2) Can a cascade set up with stationary casing wall rank different designs? 3) How do the effects of the casing motion depend on tip design configurations? A combined experimental and CFD study on several high pressure blade tip configurations is conducted to address these issues. Firstly, extensive experimental tests with aerodynamic loss and heat transfer measurement in a high speed linear cascade have been carried out for a squealer tip configuration at engine representative aerodynamic conditions. A systematic validation of the CFD solver (Rolls-Royce HYDRA) is presented, which serves as a basis for the computational analyses of the effects of the relative casing motion. Two tip configurations (squealer and flat tip) at three tip gaps (0.5%, 1.0%, 1.5% span) are analysed. The main aerodynamic impact of the casing motion is seen to promote the passage vortex, which consequently supresses the pitchwise reach of the tip leakage vortex. Inside the tip gap, the behaviour is dominated by the extra wall friction in relation of the inertia of the bulk fluid through the gap. As such, the moving casing effect is particularly strong for the flat tip at a small tip gap. For the large and medium tip gaps, both stationary and moving casing results are shown to consistently capture the trends in overall aerothermal performances. The present results confirm that even with relative casing motion, there is still a significant portion of transonic flow over a blade tip. For both the stationary and moving casing cases, the gap dependence of the over-tip heat transfer shows opposite trends for the transonic and subsonic regions respectively. The gap dependence of the blade tip heat transfer is shown to be clearly dependent on tip geometry configurations, as the bulk flow in a squealer cavity is subsonic regardless of the tip gap size, whilst the local flow state over a flat tip is much more responsive to the change of gap size.
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Coull, John D., and Nicholas R. Atkins. "The Influence of Boundary Conditions on Tip Leakage Flow." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2057.

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Most of the current understanding of tip leakage flows has been derived from detailed cascade experiments. However, the cascade model is inherently approximate since it is difficult to simulate the boundary conditions present in a real machine, particularly the secondary flows convecting from the upstream stator row and the relative motion of the casing and blade. This problem is further complicated when considering the high pressure turbine rotors of aero engines, where the high Mach numbers must also be matched in order to correctly model the aerodynamics and heat transfer. More realistic tests can be performed on high-speed turbines, but the experimental fidelity and resolution achievable in such set-ups is limited. In order to examine the differences between cascade models and real-engine behavior, the influence of boundary conditions on the tip leakage flow in an unshrouded high pressure turbine rotor is investigated using RANS calculations. This study examines the influence of the rotor inlet condition and relative casing motion. A baseline calculation with a simplified inlet condition and no relative endwall motion exhibits similar behavior to cascade studies. Only minor changes to the leakage flow are induced by introducing either a more realistic inlet condition or relative casing motion. However when both of these conditions are applied simultaneously the pattern of leakage flow is very different, with ingestion of flow over much of the early suction surface. The paper explores the physical processes driving this change and the impact on leakage losses and modeling requirements.
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Naresh Babu, K., A. Kushari, and C. Venkatesan. "Effect of Adjacent Blade Motion on the Aerodynamics of a Linear Cascade Blade." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-68666.

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Due to the trend of increasing power and reducing weight, the fan and compressor blades of turbo machinery might be more sensitive to flutter, which must strictly be avoided in the design process. In order to increase our understanding of the flutter phenomena for fan and compressor cascades, aero-elastic investigations are essential. In the present work experiments were performed in the specifically designed Oscillating Cascade Facility to investigate and quantify the unsteady aerodynamics forces and moments acting on a blade in a linear cascade of blades when the instrumented blade is stationary and the two adjacent blades on both sides of the instrumented blade are executing torsion-mode oscillations about their mid-chord. A 5-component strain gage balance was used to measure the unsteady aerodynamic forces on the model blade. The forces were measured for six inter-blade phase angles (i.e., the phase angle between the moving blade motions at a given frequency where the central blade is stationary) at low subsonic conditions, different reduced frequencies and different stagger. The time-variant forces were analyzed and variation of lift and drag coefficients for different inter-blade phase angles and reduced frequencies were plotted. The experimental results indicate that the inter-blade phase angle had a major effect on the variation of the unsteady forces and that reduced frequency had a somewhat less significant effect. Also in order to investigate the influence of the reduced frequency and inter-blade phase angles on the global stability of the cascade and its local contributions, experiments were performed for different reduced frequencies and phase angles. At the higher inter-blade phase angles (180°) the blade remains aerodynamically stable at 0° stagger, but the stability reduces at higher stagger angles. The blade is usually unstable when the interblade phase angle is 0°. At different flow conditions, some of the inter-blade phase angles appear to be aerodynamically unstable.
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Avalos, Javier, Raghavendra Murthy, X. Q. Wang, and Marc P. Mignolet. "On the Effects of Blade-Disk Interface Mistuning on the Response of Integrated Bladed Rotors." In ASME 2013 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/detc2013-13352.

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The response of blades in bladed disks can be represented as a sum of modal contributions from their cantilevered modes and a component induced by the motion of the disk and its interface with the blades. This last contribution referred to here as the disk-induced blade motions is generally considered to be tuned when performing mistuning analysis of bladed disks. Yet, as most of the blade properties, its structural coupling to the disk is likely to be uncertain, for example due to variations in thickness at the blade filet. One thus expects a mistuning of the interface stiffness and mass matrices in particular. The effect of this mistuning on the blade response, which does not appear to have received significant attention, is the focus of the present investigation. A Craig-Bampton methodology is introduced to highlight the disk-blade interface and a mistuning modeling of its stiffness matrix is introduced following the nonparametric modeling method. The analysis with various mistuning models is carried out on a 15-blade impeller finite element model at several resonances. It is found that a small mistuning of the disk-induced blade does not alter notably the mistuned response of the blades.
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Tamai, Ryoji, Ryozo Tanaka, Yoshichika Sato, Karsten Kusterer, Gang Lin, Martin Kemper, and Lars Panning-von Scheidt. "Vibration Analysis of Shrouded Turbine Blades for a 30 MW Gas Turbine." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2014.

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Turbine blades are subjected to high static and dynamic loads. In order to reduce the vibration amplitude means of friction damping devices have been developed, e.g. damping wires, interblade friction dampers and shrouds. This paper presents both numerical and experimental results for investigating the dynamical behavior of shrouded turbine blades. The studies are focused on the lowest family of the bladed disk. The aspect of experimental studies, the effect of the shroud contact force on the resonance frequency of the blade was examined by using the simplified blade test stand. Based on the result of the simplified blade studies, the shroud contact force of the real blade was determined in order to stabilize the resonance frequencies of the bladed disk system. The resonance frequencies and mode shapes of the real bladed disk assembly were measured in no rotation and room temperature condition. Finally, the dynamic strains were measured in the actual engine operations by using a telemetry system. The aspect of analytical studies, a non-linear vibration analysis code named DATES was applied to predict vibration behavior of a shrouded blade model which includes contact friction surfaces. The DATES code is a forced response analysis code that employs a 3-dimensional friction contact model. The Harmonic Balance Method (HBM) is applied to solve resulting nonlinear equations of motion in frequency domain. The simulated results show a good agreement with the experimental results.
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Broek, J. J., and A. Kooijman. "Exploration of Local Blade Motions During Blade Shaping for Thick Layered Foam Cutting." In ASME 2004 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/detc2004-57784.

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The FF-TLOM (Free Form Thick Layered Object Manufacturing) technology is a Rapid Prototyping process based on flexible blade cutting of polystyrene foam. The heated blade is shaped by three parameters, which allows an infinite amount of minimum strain energy blade shapes with none, one or two inflexions. In the shaping domain stable and unstable blade shapes can exist. Stable shapes are defined as curves with none and one-inflexion and are applied for operational cutting of foam layers with the FF-TLOM technology. The tool motions are generated from the static tool poses and are calculated for a linear change of the flexible blade, when the cutting tool moves from one tool position to the next. The cutting blade is positioned to the foam slab with help of a point relative positioned on the flexible blade. The tool frame is positioned with a point fixed relatively to the tool frame. During the tool motions the blade curvature is changed and will introduce a shift of the half way point fixed on the blade (especially in the case of asymmetrical support inclinations and high curvature). Next the local displacement of the blade points in the bending plane of the blade due to blade shaping and tool pitching are quantified during the tool motions. These displacements induce an angle of attack of the blade in cutting direction, and will influence cutting speed and cutting accuracy. The quantification software is developed and will be used in the future for an overall prediction of the total tool curve displacements due to blade shaping, such as roll, pitch, yaw and linear positioning motions of the tool. A general rule for FF-TLOM cutting is minimization of all tool motions, which are not related to the forward cutting motion.
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Namba, Masanobu, and Ayumi Kubo. "Aerodynamically Coupled Flutter of Multiple Blade Rows." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50315.

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This paper deals with the aeroelastic instability of vibrating multiple blade rows under aerodynamic coupling with each other. A model composed of three blade rows, e.g., rotor-stator-rotor, in which blades of the two rotor cascades are simultaneously vibrating, is considered. The generalized aerodynamic force on a vibrating blade consists of the component induced by the vibrating motion of the blade itself and those induced by vibrations not only of other blades in the same cascade but also of blades in another cascade. To evaluate the aerodynamic forces, the unsteady lifting surface theory for the model of three blade rows is applied. The equations describing motions of blades are coupled via the aerodynamic forces. The so-called k method is applied to determine the critical flutter conditions. A numerical study has been conducted. The flutter boundaries are compared with those for a single blade row. It is shown that the effect of the aerodynamic coupling significantly modifies the critical flutter conditions.
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Acharya, Sumanta, and Louis Moreaux. "Numerical Study of the Flow Past a Turbine Blade Tip: Effect of Relative Motion Between Blade and Shroud." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-69192.

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Turbine blade tips are often the most susceptible to material failure due to the high-speed leakage flow and associated large thermal loadings. In this paper, the effect of the blade rotation and relative motion between the blade tip and shroud is studied numerically. Three different simulations have been undertaken: (1) a static case where the blade and the shroud are stationary (used as the reference case) (2) a linearly moving blade (or shroud), and (3) a rotating blade. Comparisons between cases 1 and 2 identify the effects of relative motion, while comparison between cases 2 and 3 delineate the effects of rotational Coriolis and centrifugal forces. Geometric effects were also studied through different combinations of tip gaps and squealer depths with the relative motion and rotational effects included. The calculations were done using a commercial flow solver, Fluent, using a block body-fitted mesh, Reynolds-averaged transport equations and a turbulence model. Results confirm the significant effects of the relative motion between the blade tip and shroud, and indicate that the assumption of pressure-driven leakage flows for blade tips is inappropriate. While rotational forces also play a role, the magnitude of their effects are relatively small compared to the relative motion effects. Geometric effects are also important with the lower tip clearance reducing leakage flow and allowing the tip coolant to migrate towards the SS with relative motion.
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Mononen, Teemu, Jouni Mattila, and Antti Kolu. "Blade Control for Surface Profile Tracking by Heavy-Duty Bulldozers." In ASME/BATH 2021 Symposium on Fluid Power and Motion Control. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/fpmc2021-68656.

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Abstract The bulldozer is a heavy-duty earthmoving machine used in ground surface profiling and soil manipulation. Tracking the desired surface gradients with the hydraulically actuated manipulator while compensating for the mobile base motion is important in high-performance surface grading and traction control. In this paper, we present an approach for surface elevation tracking control for earthmoving work done by bulldozers using inertial measurement units (IMUs) and roof mounted global navigation satellite system (GNSS) antennas. We use mapping between the desired surface profile and hydraulic actuator velocities using the elevation surface and its gradient, the mobile manipulator Jacobian, and mobile base pose estimation by the extended Kalman filter (EKF) framework. With the proposed method, a relatively simple low-level actuator space control scheme can produce sufficient accuracy in varying elevation requirements besides leveling work. In an experimental setup, flat and uneven surface profiles were followed with average errors below 2 cm computed using kinematics. An external GNSS survey gave a coarse verification of the actual surface profile, showing average errors below 4 cm. This paper demonstrates a blade controller on a heavy-duty tracked vehicle with high manipulator inertia, hydraulic dynamics, and body vibrations. The experimental results validate the efficacy of the proposed method, also revealing the needs for further development.
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Sextro, Walter, Karl Popp, and Ivo Wolter. "Improved Reliability of Bladed Disks due to Friction Dampers." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-189.

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Friction dampers are installed underneath the blade platforms to improve the reliability. Because of centrifugal forces the dampers are pressed onto the platforms. Due to dry friction and the relative motion between blades and dampers, energy is dissipated, which results in a reduction of blade vibration amplitudes. The geometry of the contact is in many cases like a Hertzian line contact. A three-dimensional motion of the blades results in a two-dimensional motion of one contact line of the friction dampers in the contact plane. An experiment with one friction damper between two blades is used to verify the two-dimensional contact model including microslip. By optimizing the friction dampers masses, the best damping effects are obtained. Finally, different methods are shown to calculate the envelope of a three-dimensional response of a detuned bladed disk assembly (V84.3-4th-stage turbine blade) with friction dampers.
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Звіти організацій з теми "Blade motion"

1

Fries, Joseph. The Effect of Helicopter Main Rotor Blade Damage on the Rotor Disk (Whole Rotor) Motion. Fort Belvoir, VA: Defense Technical Information Center, June 2000. http://dx.doi.org/10.21236/ada378211.

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2

Kamiya, Akira. Prediction of the Cavitation Effect on the Flow Around the Outboard Motor Propeller Blade Hydrofoil Section Using CFD. Warrendale, PA: SAE International, October 2013. http://dx.doi.org/10.4271/2013-32-9157.

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