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    Experimental and Computational Results From the NASA Lewis Low-Speed Centrifugal Impeller at Design and Part-Flow Conditions

    Source: Journal of Turbomachinery:;1996:;volume( 118 ):;issue: 001::page 55
    Author:
    R. M. Chriss
    ,
    M. D. Hathaway
    ,
    J. R. Wood
    DOI: 10.1115/1.2836607
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The NASA Lewis Low-Speed Centrifugal Compressor (LSCC) has been investigated with laser anemometry and computational analysis at two flow conditions: the design condition as well as a lower mass flow condition. Previously reported experimental and computational results at the design condition are in the literature (Hathaway et al., 1993). In that paper extensive analysis showed that inducer blade boundary layers are centrifuged outward and entrained into the tip clearance flow and hence contribute significantly to the throughflow wake. In this report results are presented for a lower mass flow condition along with further results from the design case. The data set contained herein consists of three-dimensional laser velocimeter results upstream, inside, and downstream of the impeller. In many locations data have been obtained in the blade and endwall boundary layers. The data are presented in the form of throughflow velocity contours as well as secondary flow vectors. The results reported herein illustrate the effects of flow rate on the development of the through flow momentum wake as well as on the secondary flow. The computational results presented confirm the ability of modern computational tools to model the complex flow in a subsonic centrifugal compressor accurately. However, the blade tip shape and tip clearance must be known in order to properly simulate the flow physics. In addition, the ability to predict changes in the throughflow wake, which is largely fed by the tip clearance flow, as the impeller is throttled should give designers much better confidence in using computational tools to improve impeller performance.
    keyword(s): Flow (Dynamics) , Impellers , Design , Blades , Wakes , Clearances (Engineering) , Boundary layers , Lasers , Compressors , Equipment and tools , Shapes , Physics , Momentum AND Velocimeters ,
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      Experimental and Computational Results From the NASA Lewis Low-Speed Centrifugal Impeller at Design and Part-Flow Conditions

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/117893
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    • Journal of Turbomachinery

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    contributor authorR. M. Chriss
    contributor authorM. D. Hathaway
    contributor authorJ. R. Wood
    date accessioned2017-05-08T23:52:01Z
    date available2017-05-08T23:52:01Z
    date copyrightJanuary, 1996
    date issued1996
    identifier issn0889-504X
    identifier otherJOTUEI-28648#55_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/117893
    description abstractThe NASA Lewis Low-Speed Centrifugal Compressor (LSCC) has been investigated with laser anemometry and computational analysis at two flow conditions: the design condition as well as a lower mass flow condition. Previously reported experimental and computational results at the design condition are in the literature (Hathaway et al., 1993). In that paper extensive analysis showed that inducer blade boundary layers are centrifuged outward and entrained into the tip clearance flow and hence contribute significantly to the throughflow wake. In this report results are presented for a lower mass flow condition along with further results from the design case. The data set contained herein consists of three-dimensional laser velocimeter results upstream, inside, and downstream of the impeller. In many locations data have been obtained in the blade and endwall boundary layers. The data are presented in the form of throughflow velocity contours as well as secondary flow vectors. The results reported herein illustrate the effects of flow rate on the development of the through flow momentum wake as well as on the secondary flow. The computational results presented confirm the ability of modern computational tools to model the complex flow in a subsonic centrifugal compressor accurately. However, the blade tip shape and tip clearance must be known in order to properly simulate the flow physics. In addition, the ability to predict changes in the throughflow wake, which is largely fed by the tip clearance flow, as the impeller is throttled should give designers much better confidence in using computational tools to improve impeller performance.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleExperimental and Computational Results From the NASA Lewis Low-Speed Centrifugal Impeller at Design and Part-Flow Conditions
    typeJournal Paper
    journal volume118
    journal issue1
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2836607
    journal fristpage55
    journal lastpage65
    identifier eissn1528-8900
    keywordsFlow (Dynamics)
    keywordsImpellers
    keywordsDesign
    keywordsBlades
    keywordsWakes
    keywordsClearances (Engineering)
    keywordsBoundary layers
    keywordsLasers
    keywordsCompressors
    keywordsEquipment and tools
    keywordsShapes
    keywordsPhysics
    keywordsMomentum AND Velocimeters
    treeJournal of Turbomachinery:;1996:;volume( 118 ):;issue: 001
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
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