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Tuesday, November 24, 2020 | History

3 edition of Forced response analysis of an aerodynamically detuned supersonic turbomachine rotor found in the catalog.

Forced response analysis of an aerodynamically detuned supersonic turbomachine rotor

Forced response analysis of an aerodynamically detuned supersonic turbomachine rotor

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  • 13 Currently reading

Published by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Aeroelasticity.,
  • Unsteady flow (Aerodynamics)

  • Edition Notes

    StatementDaniel Hoyniak and Sanford Fleeter.
    SeriesNASA technical memorandum -- 87093.
    ContributionsFleeter, Sanford., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15282900M


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Forced response analysis of an aerodynamically detuned supersonic turbomachine rotor Download PDF EPUB FB2

In this paper, an analysis is developed to predict the flow-induced forced response behavior of an aerodynamically detuned rotor operating in a supersonic flow with a subsonic axial component. The aerodynamic detuning is achieved by alternating the circumferential spacing of adjacent rotor ://   Forced response analysis of an aerodynamically detuned supersonic turbomachine rotor High performance aircraft-engine fan and compressor blades are vulnerable to aerodynamically forced vibrations generated by inlet flow distortions due to wakes from upstream blade and vane rows, atmospheric gusts, and maldistributions in inlet ducts.

In this report, an analysis is developed to Get this from a library. Forced response analysis of an aerodynamically detuned supersonic turbomachine rotor.

[Daniel Hoyniak; Sanford Fleeter; United States. National Aeronautics and   Forced Response Analysis of an Aerodynamically Detuned Super­ sonic Turbomachine Rotor (NASA-TM) FORCED RESPONSE ANALYSIS OF N AN AERODYNAMICAILY DETUNED SUPERSONIC TURBOMACHINE ROTOR (NASA) 24 p.

HC A02/IF A01 CSCL 01A Unclas G33/02 Daniel Hoyniak. Lewis Research Center Cleveland, Ohio. and. Sanford Fleeter   Specific topics discussed include the response of mistuned bladed disk assemblies; forced response analysis of an aerodynamically detuned supersonic turbomachine rotor; dynamic analysis of blade groups using component mode synthesis; and pendulum dynamic vibration absorbers for reducing blade vibration in industrial ://?R= Specific topics discussed include the response of mistuned bladed disk assemblies; forced response analysis of an aerodynamically detuned supersonic turbomachine rotor; dynamic analysis of blade groups using component mode synthesis; and pendulum dynamic vibration absorbers for reducing blade vibration in industrial n° 4 analysis of forced response of Forced response analysis of an aerodynamically detuned supersonic turbomachine rotor book blade rows boundary condition that changes is that requiring the normal flow velocity to be equal to the airfoil velocity on the airfoil surface The first International Symposium on Unsteady Aerodynamics and Aero­ elasticity of Turbomachines was held in Paris inand was followed by symposia at Lausanne inCambridge inAachen inBei­ jing inand Notre Dame in A comprehensive coverage of the key physical concepts that govern gas turbine propulsion systems.

Topics include combustion technology, engine/airplane performance matching, inlets and inlet/engine integration, variable convergent/divergent nozzle aerodynamics, and ://   UNK the.

of and in " a to was is) (for as on by he with 's that at from his it an were are which this also be has or: had first one their its new after but who not they have – ; her she ' two been other when there all % during into school time may years more most only over city some world would where later up such used many can state about national out known university united then made   A higher order technique to compute the statistics of forced response of a mistuned bladed disk assembly Journal of Sound and Vibration, Vol.

No. 2 Oscillating aerodynamics and flutter of an aerodynamically detuned cascade in an incompressible flow   A mathematical model is developed to analyze the aerodynamically forced response characteristics of a detuned rotor operating in a supersonic inlet flow field with a supersonic axial component.

Alternate blade aerodynamic detuning is considered, with the aerodynamic detuning accomplished by alternating the circumferential spacing of adjacent :// Forced Response Analysis of an Aerodynamically Detuned Supersonic Turbomachine Rotor. Article. To predict the aerodynamically forced response of an airfoil, an energy balance between the   Forced response is a critical concern in turbomachinery design, as it can quickly lead to high-cycle fatigue failure.

However, for modern compressor design programs, it is virtually impossible to remove all resonant crossings that occur within the operating range of the :// The book includes 34 revised and edited articles on aeroelasticity of blades, gas-dynamics of vibrating bladerows, rotor{stator interaction, aeroacoustics, and unsteady aerodynamics of turbomachines.

The book is published in connection with the 11th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of ?dsource=recommend. Application of the Riccati Method to Rotor Dynamic Analysis of Long Shafts on a Flexible Foundation J.

Lund, Z. Wang J. Vib., Acoust., Stress, and :// Hence, the MRF is often referred to as the “frozen rotor approach.” Release c ANSYS, Inc. Janu Flow in Multiple Rotating Reference FramesWhile the MRF approach is clearly an approximation, it can provide a reasonable modelof the flow for many ://   Finally, for this section, the unsteady response of the blades for all nodal diameters are computed.

Shown in Fig. 4 are the real and imaginary parts of the modal force for different traveling wave indices. Note that for a frequency tuned and aerodynamically symmetric rotor the traveling wave index is equal to the nodal ://   Flutter onset is one of the major causes for increased vibration levels in low pressure turbine (LPT) rotor blades.

This paper describes the design process and the experimental testing of intentional mistuning patterns specifically chosen to show the possibility to control the flutter characteristics of an LPT ://   Flutter control of incompressible flow turbomachine blade rows by splitter blades Hsiao-Wei Chiang, Sanford Fleeter forced response [10, iii-However, these studies are based on classical linear theory, with the steady flow assumed to be aerodynamically detuned rotor.

The flow field is assumed to be linearly comprised of a steady NOISE FROM INDUSTRIAL PLANTS DECEM Prepared by L. GOODFRIEND ASSOCIATES under CONTRACT for the U.S. Environmental Protection Agency Office of Noise Abatement and Control Washington, D.C.

This report has been approved for general availability, The contents of this report reflect the views of- the contractor, who is responsible for the ?Dockey= 8 _0 •g - B g c c - Grain/10 SCF Ductile Blade Material Erosion rate in stator as a function of axial position Rotor Axial Distant*, Inches Erosion rate in rotor as a function of axial position Fig.

10 - Calculated erosion of 1st stage stator vane and rotor blade pressure surface - electric utility gas ?Dockey=ITXT. 02 C - Acoustic Scene Analysis: Fundamentals and Applications 02 E - Microphone array systems and methods. 03 D - Mechanisms of underwater hearing. 03 W - General 'Animal Bioacoustics' 04 A - Prediction methods for sound insulations 1.

06 B - Archeoacoustics. 08 B - Policy and regulation for recreational noise / noise in buildings Outer Front Cover; Contents; Publisher's Letter: Highlights of the PDFs on USB; Feature: Stealth Technology by Dr David Maddison ; Project: YOU can anodise aluminium at ?res=nonflash.

Abstract. Splitter blades as a passive flutter control technique is investigated by developing a mathematical model to predict the stability of an aerodynamically loaded splattered-rotor operating in an incompressible flow ://   Propulsion 2 notes 1.

Unit-1 AIRCRAFT GAS TURBINES Impulse and reaction blading of gas turbines – Velocity triangles and power output – Elementary theory – Vortex theory – Choice of blade profile, pitch and chord – Estimation of stage performance – Limiting factors in gas turbine design- Overall turbine performance – Methods of blade cooling – Matching of Vibration Analysis of Rotor - Coupling - Bearing System With Misaligned Shafts.

A Linearized Unsteady Aerodynamic Analysis for Real Blade Supersonic Cascades. Matthew D. Montgomery, Joseph M. Verdon, Inlet Distortion Generated Forced Response of a A 'trend analysis' was done after each protracted supersonic flight, where engine parameters were input into a propiatry RR computer program, that was able to detect step changes in the figures, and if this were the case, more boroscope inspections were carried :// In addition, she has contributed to the fields of flow control, global stability analysis, synthetic jets, analysis of flow structures in complex flows (transitional and turbulent) using data-driven methods, and prediction of temporal patterns using machine learning and soft computing :// TURBAN Turbomachine Design Code LEW TURBAN analysis is performed at the arithmetic mean diameter.

The stage velocity diagrams are either all similar (therefore have the same work factor) or are determined from an input stage work split. All stages have the same stator exit angle. Stage-by-stage tailoring of the velocity diagrams is not ANALGESIC Analgesia Analgesics Analgetic Analgetics Antalgic Antalgics ANALGIN ANALOGOUS Analogy ANALOGUE Analog Analogs Analogues ANALOGUE-DIGITAL A-D Analog-digital Analog-to-digital Analogue-to-digital ANALYSE Analysable Analysed Analyser Analysers Analyses Analysing Analysis Analytical Analytically ANALYTE Analytes [91] ANAMORPHIC A middle layer (22) having partitioned cavities (28) is sandwiched between an imperforate sheet (24) and an optional perforate sheet (26) to form a low resistance acoustic liner (22).

A preferred method of manufacture of the low resistance acoustic liner (20) uses aspects of the buried septum technique including placing an uncured imperforate septum (36) between a support layer (32) and a INCOMPRESSIBLE FLUID ANALYSIS The performance of a turbomachine can now be expressed in terms of the control variables, geometric variables, and fluid properties.

For the hydraulic pump it is convenient to regard the net energy transfer gH, the efficiency η, and power supplied P as dependent variables and to write the three functional This book describes the analysis and behavior of internal flows encountered in propulsion systems, fluid machinery (comp 93 5MB Pages Page size x pts Year / - system for specifying an installation position of rotor blades, securing element, rotor blade, turbomachine, and method 2 Christian Farhad Example: analysis of beam response data To demonstrate the effectiveness of time–frequency representations, we shall consider the analysis of the data shown in Figure These data were collected from an accelerometer attached to a beam.

The beam had one end free and one end embedded in sand; the sand provides a near-anechoic :// Inlet Guide Vane Wakes Including Rotor Effects. NASA Astrophysics Data System (ADS) Johnston, R.

T.; Fleeter, S. Fundamental experiments are described directed at the investigation of forcing functions generated by an inlet guide vane (IGV) row, including interactions with the downstream rotor, for application to turbomachine forced response design ://+inlet+   The current analysis extends this tuned isolated cascade theory to consider coupled aerodynamically detuned cascades where aerodynamic detuning is accomplished by changing the chord of alternate rotor blades and stator vanes.

In a coupled cascade analysis, the configuration of the rotor influences the downstream acoustic response of the stator +generated+.