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  • 1
    Publication Date: 2016-06-07
    Description: Static aerothermoelastic design/analysis of axial-flow compressors, modal flutter analysis of axial-flow turbomachines, forced vibration analysis of rotating cyclic structures and modal flutter analysis of advanced turbopropellers with highly swept blades are four new capabilities developed and implemented in NASTRAN Level 17.7. The contents, applicability and usefulness of these capabilities which were developed and documented under the sponsorship of NASA's Lewis Research Center are discussed. Overall flowcharts and selected examples are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: COSMIC Twelfth NASTRAN (R) Users' Colloq.; p 237-256
    Format: application/pdf
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  • 2
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    In:  CASI
    Publication Date: 2016-06-07
    Description: A new module, MODB, for the data reduction of NASTRAN results is described. NASTRAN analysis results can be filtered and sorted for minimum/maximum values and the printed output resulting from large NASTRAN runs can be limited based on a number of available user options. The sorting is done on stresses, forces and vector quantities like displacements, velocity, and acceleration. The module can be accessed via DMAP alters to existing rigid formats, and has been used on a large number of statics and dynamics problems resulting in considerable savings in cost, time, and the amount of printing.
    Keywords: STRUCTURAL MECHANICS
    Type: COSMIC 13th NASTRAN (R) Users' Colloq.; p 177-187
    Format: application/pdf
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  • 3
    Publication Date: 2016-06-07
    Description: An alternative method of analysis to determine the dynamic response of structures subjected to base accelerations is presented. The method is exact as opposed to the approximate technique of using unusually large masses and loads to enforce desired base accelerations. This paper presents the relevant equations to motion, ALTERs for direct and modal frequency-, random- and transient-response rigid formats, and illustrative examples.
    Keywords: STRUCTURAL MECHANICS
    Type: COSMIC 11th NASTRAN User's Colloq.; p 89-112
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  • 4
    Publication Date: 2016-06-07
    Description: An equivalence between temperature and pressure, heat conduction and stiffness and heat capacity and mass is defined, enabling acoustical modal analysis of arbitrary three dimensional volumes. The transient heat transfer analysis rigid format in NASTRAN, RF9, has been altered providing the acoustical analysis capability. Examples and ALTERs are included.
    Keywords: STRUCTURAL MECHANICS
    Type: COSMIC 11th NASTRAN User's Colloq.; p 82-88
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  • 5
    Publication Date: 2019-06-28
    Description: A new capability was added to the general purpose finite element program NASTRAN Level 17.7 to conduct forced vibration analysis of tuned cyclic structures rotating about their axis of symmetry. The effects of Coriolis and centripetal accelerations together with those due to linear acceleration of the axis of rotation were included. The theoretical, user's, programmer's and demonstration manuals for this new capability are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-165429 , NAS 1.26:165429 , D2536-941007
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  • 6
    Publication Date: 2019-06-28
    Description: A computer program based on state of the art compressor and structural technologies applied to bladed shrouded discs was developed and made operational in NASTRAN level 16. The problems encompassed include aeroelastic analyses, modes, and flutter. The demonstration manual updates are described.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-159826 , D2536-941005
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  • 7
    Publication Date: 2019-06-28
    Description: The programming routines for the NASTRAN Level 16program are presented. Particular emphasis is placed on its application to aeroelastic analyses, mode development, and flutter analysis for turbomachine blades.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-159825 , D2536-941004
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  • 8
    Publication Date: 2019-06-28
    Description: The NASTRAN aeroelastic and flutter capability was extended to solve a class of problems associated with axial flow turbomachines. The capabilities of the program are briefly discussed. The aerodynamic data pertaining to the bladed disc sector, the associated aerodynamic modeling, the steady aerothermoelastic 'design/analysis' formulations, and the modal, flutter, and subcritical roots analyses are described. Sample problems and their solutions are included.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-159824 , D2536-941003
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  • 9
    Publication Date: 2019-06-28
    Description: Theoretical aspects of a new capability, developed and added to the general purpose finite element program NASTRAN Level 17.7, to conduct forced vibration analysis of turned cyclic structures rotating about their axis of symmetry, are presented. The effects of Coriolis and centripetal accelerations as well as those due to the translational acceleration of the axis of rotation, are included. The equations of motion are first derived for an arbitrary grid point of the cyclic sector finite element model and then extended for the complete model. The equations are solved by four principal steps: (1) transformation of applied loads at frequency-dependent circumferential harmonic components; (2) application of circumferential harmonic-dependent intersegment compatibility constraints; (3) solution of frequency-dependent circumferential harmonic components of displacements; and (4) recovery of frequency-dependent response in various segments of the total structure. Five interrelated examples are presented to illustrate the various features of the development.
    Keywords: STRUCTURAL MECHANICS
    Type: ASME PAPER 83-DET-20
    Format: text
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  • 10
    Publication Date: 2019-07-13
    Description: Theoretical aspects of a new capability developed and implemented in NASTRAN level 17.7 to analyze forced vibration of a cyclic structure rotating about its axis of symmetry are presented. Fans, propellers, and bladed shrouded discs of turbomachines are some examples of such structures. The capability includes the effects of Coriolis and centripetal accelerations on the rotating structure which can be loaded with: (1) directly applied loads moving with the structure and (2) inertial loas due to the translational acceleration of the axis of rotation (''base' acceleration). Steady-state sinusoidal or general periodic loads are specified to represent: (1) the physical loads on various segments of the complete structure, or (2) the circumferential harmonic components of the loads in (1). The cyclic symmetry feature of the rotating structure is used in deriving and solving the equations of forced motion. Consequently, only one of the cyclic sectors is modelled and analyzed using finite elements, yielding substantial savings in the analysis cost. Results, however, are obtained for the entire structure. A tuned twelve bladed disc example is used to demonstrate the various features of the capability.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-173821 , NAS 1.26:173821 , ASME Conf. on Mech. Vibration and Noise; Sep 01, 1983; Dearborn, MI; United States
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