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    Axial Compressor Stator Aerodynamics

    Source: Journal of Engineering for Gas Turbines and Power:;1985:;volume( 107 ):;issue: 002::page 485
    Author:
    H. D. Joslyn
    ,
    R. P. Dring
    DOI: 10.1115/1.3239754
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Axisymmetric, through-flow calculations, currently the “backbone” of most multistage turbomachinery design systems, are being pushed to their limit. This is due to the difference between the complex, three-dimensional flows that actually occur in turbomachinery and the two-dimensional flow assumed in this type of analysis. To foster the development of design analyses that account more accurately for these three-dimensional effects, there is a need for detailed flow field data in a multistage environment. This paper presents a survey of the initial results from a detailed experimental study of the aerodynamics of the second stage of a large scale, two-stage axial compressor. Data were acquired over a range of flow coefficients. The data presented here are for the second stator and include airfoil and endwall flow visualization, and radial-circumferential traverse measurements presented in the form of fullspan contour plots of total pressure. Also presented are the spanwise distributions of total and static pressures, axial velocity, air angles, and blockage. The effect of increased loading on the growth of the hub corner stall and its impact on these parameters is discussed.
    keyword(s): Aerodynamics , Compressors , Stators , Flow (Dynamics) , Turbomachinery , Design , Airfoils , Flow visualization , Corners (Structural elements) , Pressure AND Measurement ,
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      Axial Compressor Stator Aerodynamics

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    http://yetl.yabesh.ir/yetl1/handle/yetl/99849
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    • Journal of Engineering for Gas Turbines and Power

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    contributor authorH. D. Joslyn
    contributor authorR. P. Dring
    date accessioned2017-05-08T23:20:12Z
    date available2017-05-08T23:20:12Z
    date copyrightApril, 1985
    date issued1985
    identifier issn1528-8919
    identifier otherJETPEZ-26618#485_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/99849
    description abstractAxisymmetric, through-flow calculations, currently the “backbone” of most multistage turbomachinery design systems, are being pushed to their limit. This is due to the difference between the complex, three-dimensional flows that actually occur in turbomachinery and the two-dimensional flow assumed in this type of analysis. To foster the development of design analyses that account more accurately for these three-dimensional effects, there is a need for detailed flow field data in a multistage environment. This paper presents a survey of the initial results from a detailed experimental study of the aerodynamics of the second stage of a large scale, two-stage axial compressor. Data were acquired over a range of flow coefficients. The data presented here are for the second stator and include airfoil and endwall flow visualization, and radial-circumferential traverse measurements presented in the form of fullspan contour plots of total pressure. Also presented are the spanwise distributions of total and static pressures, axial velocity, air angles, and blockage. The effect of increased loading on the growth of the hub corner stall and its impact on these parameters is discussed.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleAxial Compressor Stator Aerodynamics
    typeJournal Paper
    journal volume107
    journal issue2
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.3239754
    journal fristpage485
    journal lastpage492
    identifier eissn0742-4795
    keywordsAerodynamics
    keywordsCompressors
    keywordsStators
    keywordsFlow (Dynamics)
    keywordsTurbomachinery
    keywordsDesign
    keywordsAirfoils
    keywordsFlow visualization
    keywordsCorners (Structural elements)
    keywordsPressure AND Measurement
    treeJournal of Engineering for Gas Turbines and Power:;1985:;volume( 107 ):;issue: 002
    contenttypeFulltext
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