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    Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing

    Source: Journal of Engineering for Gas Turbines and Power:;1985:;volume( 107 ):;issue: 002::page 354
    Author:
    D. C. Wisler
    DOI: 10.1115/1.3239730
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: A systematic procedure for reducing losses in axial-flow compressors is presented. In this procedure, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles. This model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers, flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high-speed compressors. Design modifications are made by using custom-tailored airfoils and vector diagrams, airfoil endbends, and modified wall geometries in the high-loss regions. The design improvements resulting in reduced loss or increased stall margin are then scaled to high speed. This paper describes the procedure and presents experimental results to show that in some cases endwall loss has been reduced by as much as 10 percent, flow separation has been reduced or eliminated, and stall margin has been substantially improved by using these techniques.
    keyword(s): Compressors , Testing , Axial flow , Flow separation , Design , Airfoils , Leakage , Mechanisms , Boundary layers , Flow (Dynamics) AND Measurement ,
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      Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing

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    http://yetl.yabesh.ir/yetl1/handle/yetl/99831
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    • Journal of Engineering for Gas Turbines and Power

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    contributor authorD. C. Wisler
    date accessioned2017-05-08T23:20:11Z
    date available2017-05-08T23:20:11Z
    date copyrightApril, 1985
    date issued1985
    identifier issn1528-8919
    identifier otherJETPEZ-26618#354_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/99831
    description abstractA systematic procedure for reducing losses in axial-flow compressors is presented. In this procedure, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles. This model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers, flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high-speed compressors. Design modifications are made by using custom-tailored airfoils and vector diagrams, airfoil endbends, and modified wall geometries in the high-loss regions. The design improvements resulting in reduced loss or increased stall margin are then scaled to high speed. This paper describes the procedure and presents experimental results to show that in some cases endwall loss has been reduced by as much as 10 percent, flow separation has been reduced or eliminated, and stall margin has been substantially improved by using these techniques.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleLoss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing
    typeJournal Paper
    journal volume107
    journal issue2
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.3239730
    journal fristpage354
    journal lastpage363
    identifier eissn0742-4795
    keywordsCompressors
    keywordsTesting
    keywordsAxial flow
    keywordsFlow separation
    keywordsDesign
    keywordsAirfoils
    keywordsLeakage
    keywordsMechanisms
    keywordsBoundary layers
    keywordsFlow (Dynamics) AND Measurement
    treeJournal of Engineering for Gas Turbines and Power:;1985:;volume( 107 ):;issue: 002
    contenttypeFulltext
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