2 edition of Flutter analysis of a transonic fan found in the catalog.
Flutter analysis of a transonic fan
by National Aeronautics and Space Administration, Glenn Research Center, Available from NASA Center for Aerospace Information, National Technical Information Service [distributor in [Cleveland, Ohio], Hanover, MD, Springfield, VA
Written in English
|Statement||R. Srivastava ... [et al.].|
|Series||NASA/TM -- 2002-211818., NASA technical memorandum -- 211818.|
|Contributions||Srivastava, R., NASA Glenn Research Center.|
|The Physical Object|
Hi all! Does anybody know if it's possible to model flutter in the new ansys I have access to both cfx and FEM solvers. I have my wing and I want to examine if there is any risk for flutter in subsonic, transonic (thypical transonic dip) and supersonic :// guide, cutting edge upper intermediate workbook, coupled fluid structure flutter analysis of a transonic fan, counseling theories for human services practitioners essential concepts and applications standards for excellence, cuaderno de ejercicios espanol para el hispanohablante,
FSLaRC: Wind Tunnels at NASA Langley Research Center. The first major U.S. Government wind tunnel became operational in and was located at the Langley Memorial Aeronautical Laboratory of the National Advisory Committee for Aeronautics (NACA), which became NASA Langley Research Center in This wind tunnel was crude when compared to the tunnels The bending mode flutter of a modern transonic fan has been studied using a quasi-three-dimensional viscous unsteady CFD code. The type of flutter in this research is that of a highly loaded blade with a tip relative Mach number just above unity, commonly referred to as transonic stall ://
Validation of numerical simulation for rotating stall in a transonic fan. M Choi, NHS Smith, M Vahdati Whole-assembly flutter analysis of a low-pressure turbine blade. AI Sayma, M Vahdati, M Imregun, JS Green. The Aeronautical Journal (), , A non-linear aeroelasticity analysis of a fan blade using ?user=Ld7aPh0AAAAJ. Full text of "Contributions of the Transonic Dynamics Tunnel to the Testing of Active Control of Aeroelastic Response" See other formats ^J AMAA Al AA Contributions of the Transonic Dynamics Tunnel to the Testing of Active Control of Aeroelastic Response Boyd Perry, III, Thomas E. Noll, and Robert C. Scott NASA Langley Research Center, Hampton, VA AIAA Dynamics
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This paper describes the calculation of flutter stability characteristics for a transonic forward swept fan configuration using a viscous aeroelastic analysis program. Unsteady Navier-Stokes equations are solved on a dynamically deforming, body fitted, grid to obtain the aeroelastic characteristics using the energy exchange :// Flutter analysis of a transonic fan (OCoLC) Online version: Srivastava, R.
Flutter analysis of a transonic fan (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet Resource: All Authors / Contributors: R Srivastava; NASA Glenn Research :// Flutter analysis of a transonic fan Flutter analysis of a transonic fan book Microfiche version: Flutter analysis of a transonic fan (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File: All Authors / Contributors: R Srivastava; NASA Glenn Research Center, This paper describes numerical investigation of fan transonic stall flutter, especially focused on flutter bite.
A transonic stall flutter occurs in high loaded condition at part rotating speed. A region of the transonic stall flutter occasionally protrudes to an operating line at narrow rotational speed :// Aeroelastic flutter investigation of a three-stage transonic axial compressor rotor is discussed in this paper.
Unsteady CFD analyses were used to evaluate the flutter instability of the test The flutter analysis is performed under supersonic flow conditions (Case ). The aeroelastic solution is computed for a large number of inter-blade phase :// A nonlinear Euler analysis, which is based on the implicit time-marching procedure, is also developed and used to validate the shock capturing capabilities of the linearized Euler analysis.
Extensive studies on the flutter problem of transonic fans indicate that chordwise motion of the blade is very important to predict the correct flutter This paper describes the computational analysis of aerodynamic damping for prediction of flutter characteristics of a transonic fan stage that consists of a highly loaded rotor along with a tandem Vasanthakumar, P.
() Computation of Aerodynamic Damping for Flutter Analysis of a Transonic Fan. Proceedings of ASME Turbo ExpoGT, Vancouver, June?ReferenceID= Flutter-free operation of advanced transonic fan designs continues to be a challenging task for the designers of aircraft engines. In order to meet the demands of increased performance and lighter weight, these modern fan designs usually feature low-aspect ratio shroudless rotor blade designs that make the task of achieving adequate flutter margin even more challenging for the :// The aim of this study was to assess the capabilities of different simulation approaches to predict the flutter stability of a steam turbine rotor.
The focus here was on linear and nonlinear frequency domain solvers in combination with the energy method, which is widely used for the prediction of flutter onset. Whereas a GMRES solver was used for the linear problem, the nonlinear methods The above analysis is conducted under the assumption where the fan blades are structurally tuned.
Given that intentional mistuning is sometimes used as a means to prevent fan flutter [ 19, 20, 21 ], it is interesting to explore whether mistuning alone can lead to APD :// 2 F. MOYROUD, G. JACQUET-RICHARDE, T.
FRANSSON,ASME Paper GT, 1, 19, A modal coupling for fluid and structure analysis of turbomachines flutter application to a fan Hwang, C.
J., and Fang, J. "Transonic Stall/Choke Flutter Analysis of Cascades by a Navier-Stokes Solution-Adaptive Approach." Proceedings of the ASME International Gas Turbine and Aeroengine Congress and :// Part-speed flutter analysis of a wide-chord fan blade (J.W.
Chew, J.G. Marshall, M. Vahdati and M. Imregun). The effect of the blade vibration mode on a flutter in a transonic fan (K. Isomura). Role of shock structures in transonic fan rotor flutter (T.
Shibata and S. Kaji). Twenty-one years have passed since the first symposium in this series was held in Paris (). Since then there have been meetings in Lausanne (), Cambridge (), Aachen (), Beijing (), Notre Dame () and Fukuoka ().
During this period a tremendous development in the field › Physics › Classical Continuum Physics. Flutter analysis involves the solution of a double eigenvalue problem that can be expressed as () [ [ K ] − ω 2 [ M ] + [ Q ] ] ξ → = 0 → where [ K ] and [ M ] are the usual stiffness and mass matrices, respectively, ω is the flutter frequency, [ Q ] is the aerodynamic matrix, and ξ → is the vector of generalized :// American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA A Modal Coupling for Fluid and Structure Analysis of Turbomachine Flutter Application to a Fan Stage, ASME Paper, 96 - GT -  Rządkowski, R.: Dynamics of Steam Turbine Blading, Part Two Bladed Discs, Ossolineum, Wrocław - Warszawa, Conceptual Flutter Analysis of Labyrinth Seals Using Analytical Models: Part II — Physical Interpretation The Influence of Circumferential Grooves on the Flutter Stability of a Transonic Fan.
Matthias Kniefs, Martin Lange, Ronald Mailach, Flutter Analysis of a Flexible UHBR Fan at Different Flight Conditions. Matthias Schuff, Jannik. Bibliography Includes bibliographical references. Contents. Foreword. Preface. Part 1: Flutter-Flutter boundaries for pairs of low pressure turbine blades-Influence of a vibration amplitude-A method to assess flutter stability of complex modes-Flutter design of low pressure turbine blades with cyclic symmetric modes-Experimental and numerical investigation of 2D palisade flutter for the However, they predicted a significantly higher flutter margin for F2 than for Fan F1, while rig tests showed that the two blades had similar flutter margins.
A new set of flutter computations for both blades using the whole LP domain (intake, fan, OGV and ESS) was therefore Table of Contents. Foreword. Preface. Part 1: Flutter-Flutter boundaries for pairs of low pressure turbine blades-Influence of a vibration amplitude-A method to assess flutter stability of complex modes-Flutter design of low pressure turbine blades with cyclic symmetric modes-Experimental and numerical investigation of 2D palisade flutter for the harmonic oscillations-Possibility of active