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    Axial Turbine Performance Evaluation. Part B—Optimization With and Without Constraints

    Source: Journal of Engineering for Gas Turbines and Power:;1968:;volume( 090 ):;issue: 004::page 349
    Author:
    O. E. Baljé
    ,
    R. L. Binsley
    DOI: 10.1115/1.3609212
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The maximum obtainable efficiency and associated geometry have been calculated based on the use of generalized loss correlations from Part A and are presented for full and partial admission turbines over a wide range of specific speeds. The calculated effects of varying values of Reynolds number, tip clearance, and trailing edge thickness on turbine performance are presented. Because of the anticipated difficulty in fabricating some of the optimum geometries calculated, the effects of using nonoptimum values of geometric parameters on attainable efficiency have also been investigated. The derating factor for machine Reynolds number is shown to be a strong function of specific speed, varying from 0.96 at a specific speed of 100, to 0.6 at a specific speed of 3, when Reynolds number is 105 compared to a reference value of 106 . The derating factor for tip clearance is shown to be similar to what would be expected if the clearance area were considered as a leakage area. The use of blade heights, blade numbers, rotor exit angles, and degrees of reaction varying from the optimum by 25 percent produce maximum derating factors of 0.99, 0.98, 0.985, and 0.97, respectively, when compared to full optimum values.
    keyword(s): Optimization , Turbines , Performance evaluation , Reynolds number , Clearances (Engineering) , Blades , Geometry , Thickness , Leakage , Rotors AND Machinery ,
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      Axial Turbine Performance Evaluation. Part B—Optimization With and Without Constraints

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/125689
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    • Journal of Engineering for Gas Turbines and Power

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    contributor authorO. E. Baljé
    contributor authorR. L. Binsley
    date accessioned2017-05-09T00:05:40Z
    date available2017-05-09T00:05:40Z
    date copyrightOctober, 1968
    date issued1968
    identifier issn1528-8919
    identifier otherJETPEZ-26671#349_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/125689
    description abstractThe maximum obtainable efficiency and associated geometry have been calculated based on the use of generalized loss correlations from Part A and are presented for full and partial admission turbines over a wide range of specific speeds. The calculated effects of varying values of Reynolds number, tip clearance, and trailing edge thickness on turbine performance are presented. Because of the anticipated difficulty in fabricating some of the optimum geometries calculated, the effects of using nonoptimum values of geometric parameters on attainable efficiency have also been investigated. The derating factor for machine Reynolds number is shown to be a strong function of specific speed, varying from 0.96 at a specific speed of 100, to 0.6 at a specific speed of 3, when Reynolds number is 105 compared to a reference value of 106 . The derating factor for tip clearance is shown to be similar to what would be expected if the clearance area were considered as a leakage area. The use of blade heights, blade numbers, rotor exit angles, and degrees of reaction varying from the optimum by 25 percent produce maximum derating factors of 0.99, 0.98, 0.985, and 0.97, respectively, when compared to full optimum values.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleAxial Turbine Performance Evaluation. Part B—Optimization With and Without Constraints
    typeJournal Paper
    journal volume90
    journal issue4
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.3609212
    journal fristpage349
    journal lastpage359
    identifier eissn0742-4795
    keywordsOptimization
    keywordsTurbines
    keywordsPerformance evaluation
    keywordsReynolds number
    keywordsClearances (Engineering)
    keywordsBlades
    keywordsGeometry
    keywordsThickness
    keywordsLeakage
    keywordsRotors AND Machinery
    treeJournal of Engineering for Gas Turbines and Power:;1968:;volume( 090 ):;issue: 004
    contenttypeFulltext
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