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    Study on the Turbine Vane and Blade for a 1500°C Class Industrial Gas Turbine

    Source: Journal of Engineering for Gas Turbines and Power:;1994:;volume( 116 ):;issue: 003::page 597
    Author:
    S. Amagasa
    ,
    K. Takeishi
    ,
    S. Aoki
    ,
    K. Aoyama
    ,
    H. Kawai
    ,
    K. Shimomura
    ,
    M. Kadowaki
    DOI: 10.1115/1.2906861
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: This paper describes the summary of a three-year development program for the first-stage stationary vane and rotating blade for the next generation, 1500°C class, high-efficiency gas turbine. In such a high-temperature gas turbine, the first turbine vane and blade are the most important hot parts. Full-coverage film cooling (FCFC) is adopted for the cooling scheme, and directionally solidified (DS) nickel base superalloy and thermal barrier coating (TBC) will be used to prolong the creep and thermal fatigue life. The concept of the cooling configuration, fundamental cascade test results, and material test results will be presented.
    keyword(s): Industrial gases , Turbines , Blades , Cooling , Gas turbines , Creep , Nickel , Superalloys , Cascades (Fluid dynamics) , Fatigue life , Thermal barrier coatings , Rotating blades AND High temperature ,
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      Study on the Turbine Vane and Blade for a 1500°C Class Industrial Gas Turbine

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/113549
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    • Journal of Engineering for Gas Turbines and Power

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    contributor authorS. Amagasa
    contributor authorK. Takeishi
    contributor authorS. Aoki
    contributor authorK. Aoyama
    contributor authorH. Kawai
    contributor authorK. Shimomura
    contributor authorM. Kadowaki
    date accessioned2017-05-08T23:44:07Z
    date available2017-05-08T23:44:07Z
    date copyrightJuly, 1994
    date issued1994
    identifier issn1528-8919
    identifier otherJETPEZ-26729#597_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/113549
    description abstractThis paper describes the summary of a three-year development program for the first-stage stationary vane and rotating blade for the next generation, 1500°C class, high-efficiency gas turbine. In such a high-temperature gas turbine, the first turbine vane and blade are the most important hot parts. Full-coverage film cooling (FCFC) is adopted for the cooling scheme, and directionally solidified (DS) nickel base superalloy and thermal barrier coating (TBC) will be used to prolong the creep and thermal fatigue life. The concept of the cooling configuration, fundamental cascade test results, and material test results will be presented.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleStudy on the Turbine Vane and Blade for a 1500°C Class Industrial Gas Turbine
    typeJournal Paper
    journal volume116
    journal issue3
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.2906861
    journal fristpage597
    journal lastpage604
    identifier eissn0742-4795
    keywordsIndustrial gases
    keywordsTurbines
    keywordsBlades
    keywordsCooling
    keywordsGas turbines
    keywordsCreep
    keywordsNickel
    keywordsSuperalloys
    keywordsCascades (Fluid dynamics)
    keywordsFatigue life
    keywordsThermal barrier coatings
    keywordsRotating blades AND High temperature
    treeJournal of Engineering for Gas Turbines and Power:;1994:;volume( 116 ):;issue: 003
    contenttypeFulltext
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