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    Evaluation of Flow Field Approximations for Transonic Compressor Stages

    Source: Journal of Turbomachinery:;1997:;volume( 119 ):;issue: 003::page 445
    Author:
    D. J. Dorney
    ,
    O. P. Sharma
    DOI: 10.1115/1.2841143
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The flow through gas turbine compressors is often characterized by unsteady, transonic, and viscous phenomena. Accurately predicting the behavior of these complex multi-blade-row flows with unsteady rotor–stator interacting Navier–Stokes analyses can require enormous computer resources. In this investigation, several methods for predicting the flow field, losses, and performance quantities associated with axial compressor stages are presented. The methods studied include: (1) the unsteady fully coupled blade row technique, (2) the steady coupled blade row method, (3) the steady single blade row technique, and (4) the loosely coupled blade row method. The analyses have been evaluated in terms of accuracy and efficiency.
    keyword(s): Flow (Dynamics) , Compressors , Approximation , Blades , Stators , Gas turbines , Rotors AND Computers ,
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      Evaluation of Flow Field Approximations for Transonic Compressor Stages

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/119591
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    contributor authorD. J. Dorney
    contributor authorO. P. Sharma
    date accessioned2017-05-08T23:55:04Z
    date available2017-05-08T23:55:04Z
    date copyrightJuly, 1997
    date issued1997
    identifier issn0889-504X
    identifier otherJOTUEI-28661#445_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/119591
    description abstractThe flow through gas turbine compressors is often characterized by unsteady, transonic, and viscous phenomena. Accurately predicting the behavior of these complex multi-blade-row flows with unsteady rotor–stator interacting Navier–Stokes analyses can require enormous computer resources. In this investigation, several methods for predicting the flow field, losses, and performance quantities associated with axial compressor stages are presented. The methods studied include: (1) the unsteady fully coupled blade row technique, (2) the steady coupled blade row method, (3) the steady single blade row technique, and (4) the loosely coupled blade row method. The analyses have been evaluated in terms of accuracy and efficiency.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleEvaluation of Flow Field Approximations for Transonic Compressor Stages
    typeJournal Paper
    journal volume119
    journal issue3
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2841143
    journal fristpage445
    journal lastpage451
    identifier eissn1528-8900
    keywordsFlow (Dynamics)
    keywordsCompressors
    keywordsApproximation
    keywordsBlades
    keywordsStators
    keywordsGas turbines
    keywordsRotors AND Computers
    treeJournal of Turbomachinery:;1997:;volume( 119 ):;issue: 003
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
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