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    Stall Inception in Axial Compressors

    Source: Journal of Turbomachinery:;1990:;volume( 112 ):;issue: 001::page 116
    Author:
    N. M. McDougall
    ,
    N. A. Cumpsty
    ,
    T. P. Hynes
    DOI: 10.1115/1.2927406
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Detailed measurements have been made of the transient stalling process in an axial compressor stage. The stage is of high hub-casing ratio and stall is initiated in the rotor. If the rotor tip clearance is small stall inception occurs at the hub, but at clearances typical for a multistage compressor the inception is at the tip. The crucial quantity in both cases is the blockage caused by the endwall boundary layer. Prior to stall, disturbances rotate around the inlet flow in sympathy with rotating variations in the endwall blockage; these can persist for some time prior to stall, rising and falling in amplitude before the final increase, which occurs as the compressor stalls.
    keyword(s): Compressors , Stall inception , Rotors , Clearances (Engineering) , Boundary layers , Flow (Dynamics) AND Measurement ,
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      Stall Inception in Axial Compressors

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/107794
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    • Journal of Turbomachinery

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    contributor authorN. M. McDougall
    contributor authorN. A. Cumpsty
    contributor authorT. P. Hynes
    date accessioned2017-05-08T23:34:11Z
    date available2017-05-08T23:34:11Z
    date copyrightJanuary, 1990
    date issued1990
    identifier issn0889-504X
    identifier otherJOTUEI-28600#116_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/107794
    description abstractDetailed measurements have been made of the transient stalling process in an axial compressor stage. The stage is of high hub-casing ratio and stall is initiated in the rotor. If the rotor tip clearance is small stall inception occurs at the hub, but at clearances typical for a multistage compressor the inception is at the tip. The crucial quantity in both cases is the blockage caused by the endwall boundary layer. Prior to stall, disturbances rotate around the inlet flow in sympathy with rotating variations in the endwall blockage; these can persist for some time prior to stall, rising and falling in amplitude before the final increase, which occurs as the compressor stalls.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleStall Inception in Axial Compressors
    typeJournal Paper
    journal volume112
    journal issue1
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2927406
    journal fristpage116
    journal lastpage123
    identifier eissn1528-8900
    keywordsCompressors
    keywordsStall inception
    keywordsRotors
    keywordsClearances (Engineering)
    keywordsBoundary layers
    keywordsFlow (Dynamics) AND Measurement
    treeJournal of Turbomachinery:;1990:;volume( 112 ):;issue: 001
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
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