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Статті в журналах з теми "Transonic Cascade Flutter Study"
Lu, P. J., and S. K. Chen. "Evaluation of Acoustic Flutter Suppression for Cascade in Transonic Flow." Journal of Engineering for Gas Turbines and Power 124, no. 1 (November 1, 2000): 209–19. http://dx.doi.org/10.1115/1.1365933.
Повний текст джерелаKobayashi, H. "Annular Cascade Study of Low Back-Pressure Supersonic Fan Blade Flutter." Journal of Turbomachinery 112, no. 4 (October 1, 1990): 768–77. http://dx.doi.org/10.1115/1.2927720.
Повний текст джерелаOtt, P., A. Bo¨lcs, and T. H. Fransson. "Experimental and Numerical Study of the Time-Dependent Pressure Response of a Shock Wave Oscillating in a Nozzle." Journal of Turbomachinery 117, no. 1 (January 1, 1995): 106–14. http://dx.doi.org/10.1115/1.2835625.
Повний текст джерелаLepicovsky, J., R. V. Chima, E. R. McFarland, and J. R. Wood. "On Flowfield Periodicity in the NASA Transonic Flutter Cascade." Journal of Turbomachinery 123, no. 3 (February 1, 2000): 501–9. http://dx.doi.org/10.1115/1.1378300.
Повний текст джерелаKobayashi, H. "Unsteady Aerodynamic Damping Measurement of Annular Turbine Cascade With High Deflection in Transonic Flow." Journal of Turbomachinery 112, no. 4 (October 1, 1990): 732–40. http://dx.doi.org/10.1115/1.2927716.
Повний текст джерелаLepicovsky, Jan, David Šimurda, Jindřich Hála, Petr Šidlof, and Martin Štěpán. "Blade pressure loading and torque measurement in a transonic linear cascade." Journal of Physics: Conference Series 2511, no. 1 (May 1, 2023): 012030. http://dx.doi.org/10.1088/1742-6596/2511/1/012030.
Повний текст джерелаBakhle, Milind A., T. S. R. Reddy, and Theo G. Keith. "Subsonic/Transonic Cascade Flutter Using a Full-Potential Solver." AIAA Journal 31, no. 7 (July 1993): 1347–49. http://dx.doi.org/10.2514/3.49072.
Повний текст джерелаKobayashi, H. "Effects of Shock Waves on Aerodynamic Instability of Annular Cascade Oscillation in a Transonic Flow." Journal of Turbomachinery 111, no. 3 (July 1, 1989): 222–30. http://dx.doi.org/10.1115/1.3262259.
Повний текст джерелаMcBean, Ivan, Kerry Hourigan, Mark Thompson, and Feng Liu. "Prediction of Flutter of Turbine Blades in a Transonic Annular Cascade." Journal of Fluids Engineering 127, no. 6 (May 29, 2005): 1053–58. http://dx.doi.org/10.1115/1.2060731.
Повний текст джерелаCinnella, P., P. De Palma, G. Pascazio, and M. Napolitano. "A Numerical Method for Turbomachinery Aeroelasticity." Journal of Turbomachinery 126, no. 2 (April 1, 2004): 310–16. http://dx.doi.org/10.1115/1.1738122.
Повний текст джерелаДисертації з теми "Transonic Cascade Flutter Study"
Roy, Arnab. "Experimental Study of Gas Turbine Endwall Cooling with Endwall Contouring under Transonic Conditions." Diss., Virginia Tech, 2014. http://hdl.handle.net/10919/25801.
Повний текст джерелаPh. D.
Kullberg, James C. "An experimental and numerical study of secondary flows and film cooling effectiveness in a transonic cascade." Honors in the Major Thesis, University of Central Florida, 2011. http://digital.library.ucf.edu/cdm/ref/collection/ETH/id/454.
Повний текст джерелаB.S.M.E.
Bachelors
Engineering and Computer Science
Mechanical Engineering
Prahallada, J. "Blade Flutter in a Linear Cascade: Unsteady Loads and Flow Features in Subsonic and Transonic Flows." Thesis, 2018. https://etd.iisc.ac.in/handle/2005/4108.
Повний текст джерелаGATET initiative of AR&DB and GTRE
Yao, Lo-shan, and 姚樂山. "The Experiment of SDOF Transonic Cascade Flutter Suppression Using Active Acoustic Control ─ Cascade Flutter Experiment." Thesis, 2000. http://ndltd.ncl.edu.tw/handle/90266539357495716146.
Повний текст джерела國立成功大學
航空太空工程學系
88
Flutter is a dynamic instability due to mutual interaction among inertia, elastic, and unsteady aerodynamic forces. Single-degree-of-freedom (SDOF) flutter is a typical flutter type occurring in the transonic flow regime. The objective of the present work is to study the SDOF transonic torsional flutter of cascade via experimental method. Method of image is applied to render the single blade testing in a solid wall wind tunnel a simulation that represents a cascade flow of 180 degrees shift in interblade phase angle. The experiment was conducted in a 200 mm ´ 200 mm blow-down type transonic pilot wind tunnel. The tested Mach number ranges from 0.4 to 0.8. The experimental works include the manufacturing of a fan blade, the design and construction of a model support and safety interlock system, as well as the design of data acquisition and processing system. The present flutter experiment successfully obtained blade flutter boundaries at Mach numbers 0.404, 0.564, 0.692, 0.728, and 0.817, respectively. The test data show that the flutter boundaries exhibit “transonic dip” phenomenon and the flutter frequency approaches the blade natural vibration frequency as Mach number increases. Comparing to the perforated wall flutter experiment, the present cascade flutter shows premature transonic dip at a smaller Mach number. Moreover, the flutter frequency approaches the structural natural vibration frequency via a different route of trend.
Chen, Sen-Kuei, and 陳森貴. "ACOUSTIC FLUTTER SUPPRESSION OF CASCADE ININVISCID AND VISCOUS TRANSONIC FLOWS." Thesis, 1999. http://ndltd.ncl.edu.tw/handle/57245433871899532585.
Повний текст джерела國立成功大學
航空太空工程學系
87
The objective of this research is to evaluate numerically the transonic flutter suppression concept based on the application of sound waves to a cascade configuration. Both Euler and Navier-Stokes equations are used. The emphasis is placed on finding the basic suppression mechanism and the important physical and control parameters involved. Of particular interest is the viscous effect on the present acoustic method, which has not yet been attempted before. A high-resolution Modified Osher-Chakravarthy MUSCL type third order upwind total variation diminishing (TVD) scheme based on dynamic mesh is used as the analysis tool. Modification on the reconstruction of the cell interface values makes the present method more suitable for treating viscous and highly stretched cascade grid system. A non-reflected boundary condition capable of treating reflected outgoing and imposed incoming waves is implemented in the present code. Monopole sound source treatment is numerically designed to model the acoustic waves emitted from the solid wall. This time-accurate flow solver is validated first using various kinds of acoustic, flutter and viscous flow model problems. In a generic bending-torsion flutter study, trailing-edge is found to be the optimal forcing location and the control gain phase is crucial for an effective suppression. The P&W TS33 test cascade was used as the model to evaluate the acoustic flutter suppression technique. The analysis of blade row instability versus some discrete interblade phase angles was presented. The cases with interblade phase angle are selected to test the active acoustic method for the cascade flow. Both internal and external active excitations were applied. With an appropriate selection of the control logic the flutter margin can be enlarged. For external excitation enforced at the downstream exit plane, it is found that the critical angle of acoustic incidence inhibits certain interblade phase angle range from being controlled acoustically. Analogous to what were concluded in the isolated airfoil study, for internal excitation, trailing-edge forcing is shown to be optimal since the trailing-edge receptivity still works as the dominant mechanism for generating the acoustically-induced airloads. The influence of boundary layer effect on the acoustic excitation was explored. The vorticity blown across the boundary layer by acoustic excitation is found to be the contributing factor which causes the discrepancy of the acoustically-induced airloads between inviscid and viscous results. The effect of these ejected and induced vortices has been studied by both analytical and numerical methods. A subsequent limit cycle type transonic airfoil flutter in both inviscid and viscous flows was examined using active acoustic control technique. These results show that flutter can be suppressed at the beginning stage of the unstable motion, and the ability to suppress the instability is dependent on the energy (acoustic strength) supplied by the acoustic actuator. Reversed trend is found in viscous flutter suppression study as the gain amplitude is increased to strengthen the acoustic actuator. This is conjectured that too strong forcing might cause boundary layer separation, leading to a more complex and unstable situation than what is anticipated.
I, Su Hung, and 蘇鴻義. "The Experiment of SDOF Transonic Cascade Flutter Suppression Using Active Acoustic Control." Thesis, 2001. http://ndltd.ncl.edu.tw/handle/01966449700219802516.
Повний текст джерела國立成功大學
航空太空工程學系
89
Flutter analysis is a required step that has to be validated in the design loop of a new turboengine. Flutter suppression technology can be either passive or active. This research adopts the active method. Acoustic control technique is used here to suppress flutter instability occurring in the transonic flow. For acoustic flutter control, the primary field is that induced by the structural vibration or elastic deformation, whereas the secondary field comes from the active acoustic devices. The aerodynamic damping which is induced by the trailing-edge receptivity effect of the secondary fields holds a key role in suppressing the flutter. The experiment was conducted in a 200mm 200mm blow-down type transonic pilot wind tunnel. Flutter boundary is found in the first step, and active acoustic control is employed to suppress the flutter motion. Acoustic flutter control calls for sensitive sensor, fast-responsive sound actuator, and correct control logic including gain phase and amplitude. It has been shown previously that only when flutter instability is detected early in the beginning infinitesimal stage and a sufficient strength of sound wave can be generated with appropriate phase shift could a flutter motion be suppressed acoustically. The present work include 1) the hardware improvement of the control valve and the front setting chamber, 2) the calibration of the flutter flow field using new equipments, 3) the search of flutter boundary in transonic flow, and 4) to confirm the operation range of acoustic equipment. The objective of the present research is to study the feasibility of suppressing single-degree-of-freedom torsional flutter of a cascad flow.
Panthi, Niraj. "Shock Dynamics due to Downstream Pressure Perturbations: Idealization of Transonic Unstarted Cascade Flutter." Thesis, 2019. https://etd.iisc.ac.in/handle/2005/4723.
Повний текст джерелаLu, Feng-Tai, and 呂鋒泰. "The Experiment of SDOF Transonic Cascade Flutter Suppression - Construction of the Active Acoustic Control Facilities." Thesis, 2000. http://ndltd.ncl.edu.tw/handle/96607107588269794092.
Повний текст джерела國立成功大學
航空太空工程學系
88
Flutter analysis is a required step that has to be validated in the design loop of a new engine. Active acoustic control technique is a potential candidate that could be considered for suppressing engine blade flutter. Acoustic flutter control calls for sensitive sensor, fast-responsive sound actuator, and correct control logic including gain phase and amplitude. It has been shown previously that only when flutter instability can be detected early in the infinitesimal stage and sufficient strength of sound wave can be generated with appropriate phase shift could a flutter motion be suppressed acoustically. The objective of the present work is to develop an acoustic control device that can be applied to suppress blade flutter in a transonic wind tunnel experiment. The main design guideline lies in the direct amplification and phase shifting of the sensed flutter signals, and the use of this amplified signal to drive a loudspeaker system for flutter suppression. The tasks accomplished in the present design work include 1) a flutter test section design and manufacturing, 2) a design and validation of the flutter signal detection system and the phase changer system, and 3) the design and fabrication of a loudspeaker and the adapter system to the wind tunnel wall.
Книги з теми "Transonic Cascade Flutter Study"
Methodology of blade unsteady pressure measurement in the NASA transonic flutter cascade. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.
Знайти повний текст джерелаNational Aeronautics and Space Administration (NASA) Staff. Methodology of Blade Unsteady Pressure Measurement in the NASA Transonic Flutter Cascade. Independently Published, 2018.
Знайти повний текст джерелаЧастини книг з теми "Transonic Cascade Flutter Study"
Kaji, Shojiro. "Transonic Cascade Flutter in Combined Bending-Chordwise Translational Mode." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 783–95. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_51.
Повний текст джерелаPrasad, Chandra Shekhar, and Ludek Pesek. "Classical flutter study in turbomachinery cascade using boundary element method for incompressible flows." In Advances in Mechanism and Machine Science, 4055–64. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-20131-9_404.
Повний текст джерелаQiu, Ju, and Chaofeng Liu. "Verification and Validation of Supersonic Flutter of Rudder Model for Experiment." In Optimization Problems in Engineering [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.98384.
Повний текст джерелаТези доповідей конференцій з теми "Transonic Cascade Flutter Study"
Chenaux, Virginie Anne, and Björn Grüber. "Aeroelastic Investigation of an Annular Transonic Compressor Cascade: Numerical Sensitivity Study for Validation Purposes." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43297.
Повний текст джерелаLu, Pong-Jeu, and Sen-Kuei Chen. "Evaluation of Acoustic Flutter Suppression for Cascade in Transonic Flow." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-065.
Повний текст джерелаLepicovsky, J., E. R. McFarland, R. V. Chima, and J. R. Wood. "On Flowfield Periodicity in the NASA Transonic Flutter Cascade: Part I — Experimental Study." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0572.
Повний текст джерелаLepicovsky, J., V. R. Capece, and C. T. Ford. "Resonance Effects in the NASA Transonic Flutter Cascade Facility." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38344.
Повний текст джерелаChima, R. V., E. R. McFarland, J. R. Wood, and J. Lepicovsky. "On Flowfield Periodicity in the NASA Transonic Flutter Cascade: Part II — Numerical Study." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0573.
Повний текст джерелаWatanabe, Toshinori, Junichi Kazawa, Seiji Uzawa, and Benjamin Keim. "Numerical and Experimental Study of Active Flutter Suppression With Piezoelectric Device for Transonic Cascade." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51467.
Повний текст джерелаJutur, Prahallada, and Raghuraman N. Govardhan. "Effect of Pressure Ratio on Bending Mode Flutter in a Transonic Linear Cascade." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4569.
Повний текст джерелаKobayashi, Hiroshi. "Annular Cascade Study of Low Back-Pressure Supersonic Fan Blade Flutter." 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-297.
Повний текст джерелаPurushothaman, Kirubakaran, Sankar Kumar Jeyaraman, Sasikanta Parida, and Kishore Prasad Deshkulkarni. "Aeroelastic Flutter Analysis of Linear Cascade Blades: STC5." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4773.
Повний текст джерелаSzéchényi, Edmond. "Fan Blade Flutter: Single Blade Instability or Blade to Blade Coupling?" In ASME 1985 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-gt-216.
Повний текст джерела