3 edition of Blade row interaction effects on flutter and forced response found in the catalog.
Blade row interaction effects on flutter and forced response
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va
Written in English
|Statement||Daniel H. Buffum.|
|Series||NASA technical memorandum -- 106438., NASA technical memorandum -- 106438.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
A control system actively controls at least one troublesome mode of an unsteady motion phenomenon in turbomachinery in order to enable an increase in the operating range of the turbomachinery. For example, rotor blade flutter or rotating stall may be controlled in a turbocompressor. The control system has a control bandwidth which is at least partly coexstensive with the bandwidth of the Cited by: A.H. Epstein, M.B. Giles, T. Shang and A.K. Sehra. `Blade row interaction effects on compressor measurements'. AIAA Journal of Propulsion and Power, 9(4), A.P. Saxer and M.B. Giles. `Predictions of three-dimensional steady and unsteady inviscid transonic stator/rotor interaction with inlet radial temperature nonuniformity'.
Experiments on annular cascades. gust or forced response and flutter, with or without structural mistuning. It also prevents possible damages on the blade row in cases of flutter investigations, by limiting the vibration amplitude during unsteady measurement. The test facility casing wall is instrumented with 16 pressure taps. Show only items where. Author.
Effects of Stator Wakes and Spanwise Nonuniform Inlet Conditions on the Rotor Flow of an Axial Turbine Stage Blade Row Interaction in a Multistage Low-Pressure Turbine. N. Arndt. J. Turbomach. January , (1): – Rotor Blade Unsteady Aerodynamic Gust Response to Inlet Guide Vane Wakes. S. R. Manwaring, S. Fleeter. J. Aug 25, · On the other hand, rotating stall, blade flutter, forced blade vibration and acoustic resonance can all have more than one mode of unsteady motion and this necessitates a more complex control system if it is to adequately control all the dominant modes of an unsteady motion phenomenon over a range of operating conditions of the turbomachine.
Economic appraisal of preventing work accidents at company level.
Estimating the value of subsidies for federal loans and loan guarantees.
few remarks on the history and practice of the Court of Record for the town & borough of Southwark.
Gold Trails- How to Manual & Catalog/ Prospecting and Small Scale Mining
100 anos de historia
works of Robert Bloomfield
Catalogue of books, belonging to the Springfield Library Company, April, 1796
Honolulu Academy of Arts.
Thermophysics and temperature control of spacecraft and entry vehicles
nomenclature of primates commonly used in laboratory work
introduction to cell biology
Every man his own law-maker
Grinding It Out
Characteristic symptoms of the most important homoeopathic remedies.
Get this from a library. Blade row interaction effects on flutter and forced response. [Daniel H Buffum; United States. National Aeronautics and Space Administration.]. In this paper, we present an analysis of the unsteady aerodynamic response of cascades due to incident gusts (the forced response problem) or blade vibration (the flutter problem) when the cascade is part of a multistage fan, compressor, or cinemavog-legrauduroi.com by: Multi-row effects are shown not to be important in this case.
However, the test case serves as a validation for the implementation of the methodology and further work will focus on the implementation of several spinning modes and the computations of forced response and flutter cases with several cinemavog-legrauduroi.com by: 2.
In particular, we show that multistage effects can strongly affect the aerodynamic loads acting on a given blade row.
Furthermore, the method presented is highly efficient. For example, to perform a flutter calculation requires only about three times the CPU time of one steady flow computation for each interblade phase angle and frequency Cited by: Aug 17, · Analysis of the Effect of Multi-Row and Multi-Passage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration: Part 1 — Aerodynamic Excitation multi-row flutter calculations are performed, showing the influence of the upstream and downstream blade row onto aerodynamic cinemavog-legrauduroi.com by: 1.
The validity of the principle of superposition for forced response analysis is evaluated by its application to a research propfan stage. The counter-rotating propfan features transonic flow conditions and aerodynamic interaction between the blade rows.
The computed unsteady aerodynamics are verified by comparison with rig cinemavog-legrauduroi.com by: 6. Flutter Analysis of Contra-Rotating Blade Rows (the forced response problem) or blade vibration (the flutter problem) when the cascade is part of a multistage fan, compressor, or turbine.
Blade health monitoring of gas turbine using online crack detection The capability of the baseline CFD solver for blade row interaction flow prediction is further validated against the von. Experimental blade row interactions. Passages of preceding blade wakes and their effects in the rotor passages of a single stage axial-flow fan (T.
Adachi and Y. Yamashita). Forced response vibrations of a low pressure turbine due to circumferential temperature distortions (S.R. Manwaring and K.L. Kirkeng). The aerodynamic interaction of upstream and downstream blade rows can have a significant impact on the forced response of the compressor.
Previously, the authors carried out the forced response analysis of a three-row stator-rotor-stator (S1-R2-S2) configuration from a stage cinemavog-legrauduroi.com: Shreyas Hegde, Zhiping Mao, Tianyu Pan, Laith Zori, Rubens Campregher, Robert Kielb. Unsteady Aerodynamics and Aeroelasticity of Turbomachines Proceedings of the 8th International Symposium held in Stockholm, Sweden, 14–18 September Three Dimensional Linearized Navier-Stokes Calculations for Flutter and Forced Response.
Pages Passages of Preceding Blade Wakes and Their Effects in the Rotor Passages of a. The flutter is an aero-elastic phenomenon that is linked to the interaction of the flow and the traveling deformation wave in the cascade when only the damping of the cascade changes.
As a case study the dynamic properties of the five-blade-bunch excited by the running harmonic external forces and aerodynamic self-excited forces are cinemavog-legrauduroi.com by: 2.
The unsteady effects of this type of problem can be addressed using the harmonic method within Numeca’s FINE/TURBO code, Analysis of Unsteady Blade Row Interaction Using Nonlinear Harmonic Approach,” Three Dimensional Linearized Navier-Stokes Calculations for Cited by: 1.
This book presents the papers from the 10th International Conference on Vibrations in Rotating Machinery. This conference, first held inhas defined and redefined the state-of-the-art in the many aspects of vibration encountered in rotating machinery.
A New Reduced Order Modeling for Stability and Forced Response Analysis of Aero-Coupled Blades Considering Various Mode Families Experimental Study of Effects of Grooved Tip Clearances on the Flow Field in a Compressor Cascade Passage Effect of Hot Streak Migration on Unsteady Blade Row Interaction in an Axial Turbine.
Jenny, C. A Mistuned Forced Response Analysis of an Embedded Compressor Blisk Using a Reduced Order Model. Study of the Impact of Multi-Row Interaction on Flutter Analysis for a Representative LPT Geometry. Adrian Sotillo, Juan Manuel Numerical Investigation on Wide-Chord Fan Blade Forced Response due to Vortex Ingestion.
Zhonglin Wang, Yong. In this book, the author introduces the concept of unsteady aerodynamics and its underlying principles. He provides the readers with a comprehensive review of the fundamental physics of free and forced unsteadiness, the terminology and basic equations of aerodynamics ranging from.
Rotating stall (propagating stall) consists of large stall zones covering several blade passages. It propagates in the direction of the rotation and at some fraction of rotor speed.
The number of stall zones and the propagating rates vary considerably. Rotating stall is. The schematic in Fig. 3 illustrates two major physical processes when the upstream-going pressure waves were generated due to R2 forced-response vibrations: (1) pressure waves due to S1-wake-R2-blade interaction are generated and (2) pressure waves due to R2 blade vibration are generated.
The frequency in the rotor reference frame is denoted as. Proper Orthogonal Decomposition and Response Surface Method for TPS/RLV Structural Design and Optimization: X Case Study Turbomachinery Blade Row Interaction Aerodynamics and Forced Response Experiments.
Sandy Fleeter; ABP Aeroelasticity (Invited) • Monday, 10 January • hrs Flutter Analysis of a Rotating Blade Row. 1-Way Fluid-Structure Interaction p2 p2 p2 l 2-Way Fluid-Structure Interaction p2 4.
Transient Blade Row l Pitch Change l Time Transformation l ANSYS CFD Enterprise ANSYS CFD Premium ANSYS FLUENT CFX POLYFLOW Forte FENSAP-ICE AIM. Blade Flutter Analysis l Forced Response Analysis l Flank milled blades l.Maximum Amplification of Blade Response in Mistuned Multi Stage Assemblies.
Javier Avalos A New Reduced Order Modeling for Stability and Forced Response Analysis of Aero-Coupled Blades Considering Various Mode Families. Effect of the Structural Coupling on the Flutter Onset of a Sector of Low-Pressure Turbine Vanes.
Ruben Antona.Transient Blade Row l Pitch Change l Fourier Transformation l Harmonic Analysis l Blade Flutter Analysis l Forced Response Analysis l l= Fully Supported p= Limited Capability p= Requires more than 1 product 8 ANSYS CFD Enterprise ANSYS CFD Premium ANSYSANSYS CFDANSYS FLUENT CFX POLYFLOW Forte FLO Professional FENSAP-ICE AIM Chemkin Pro.