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    Study on Advanced Internal Cooling Technologies for the Development of Next-Generation Small-Class Aircraft Engines

    Source: Journal of Turbomachinery:;2010:;volume( 132 ):;issue: 003::page 31019
    Author:
    Yoshitaka Fukuyama
    ,
    Shu Fujimoto
    ,
    Toyoaki Yoshida
    ,
    Yoji Okita
    ,
    Takashi Yamane
    ,
    Fujio Mimura
    ,
    Masahiro Matsushita
    DOI: 10.1115/1.3151602
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: An innovative internal cooling structure named multislot cooling has been invented for high-pressure turbine (HPT) nozzles and blades. This cooling structure has been designed to be simple and inexpensive and to exhibit good cooling performance. In order to confirm the cooling performance of this structure, test pieces of dummy turbine nozzles were manufactured. Three geometric parameters (width of slots, overall height of cooling channel, and height of jet impingement) are associated with these test pieces. The cooling performance tests were conducted by using these test pieces for several Reynolds numbers of the mainstream hot gas [2.2×105–3.4×105] and cooling airflow [3×103–1×104]. Infrared images of the heated surfaces of the test pieces were captured for every Reynolds number in the tests, and then the distributions of the cooling effectiveness were obtained. Simultaneously, the pressure losses were measured. This paper describes the hot gas flow tests performed to confirm the effects of the geometric parameters on the cooling performance and pressure loss, and to obtain data of Nusselt number and pressure loss coefficient for the design of turbine nozzles in the future by applying this new cooling structure to next-generation small-class aircraft engines. Additionally a preliminary analysis of airfoil cooling was performed to evaluate both cooling performance of conventional impingement cooling and multislot cooling when applied to a HPT nozzle. As a result it was found that the multislot cooling is well applicable to cooling of HPT airfoils.
    keyword(s): Cooling , Pressure AND Nozzles ,
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      Study on Advanced Internal Cooling Technologies for the Development of Next-Generation Small-Class Aircraft Engines

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    http://yetl.yabesh.ir/yetl1/handle/yetl/145000
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    contributor authorYoshitaka Fukuyama
    contributor authorShu Fujimoto
    contributor authorToyoaki Yoshida
    contributor authorYoji Okita
    contributor authorTakashi Yamane
    contributor authorFujio Mimura
    contributor authorMasahiro Matsushita
    date accessioned2017-05-09T00:41:34Z
    date available2017-05-09T00:41:34Z
    date copyrightJuly, 2010
    date issued2010
    identifier issn0889-504X
    identifier otherJOTUEI-28764#031019_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/145000
    description abstractAn innovative internal cooling structure named multislot cooling has been invented for high-pressure turbine (HPT) nozzles and blades. This cooling structure has been designed to be simple and inexpensive and to exhibit good cooling performance. In order to confirm the cooling performance of this structure, test pieces of dummy turbine nozzles were manufactured. Three geometric parameters (width of slots, overall height of cooling channel, and height of jet impingement) are associated with these test pieces. The cooling performance tests were conducted by using these test pieces for several Reynolds numbers of the mainstream hot gas [2.2×105–3.4×105] and cooling airflow [3×103–1×104]. Infrared images of the heated surfaces of the test pieces were captured for every Reynolds number in the tests, and then the distributions of the cooling effectiveness were obtained. Simultaneously, the pressure losses were measured. This paper describes the hot gas flow tests performed to confirm the effects of the geometric parameters on the cooling performance and pressure loss, and to obtain data of Nusselt number and pressure loss coefficient for the design of turbine nozzles in the future by applying this new cooling structure to next-generation small-class aircraft engines. Additionally a preliminary analysis of airfoil cooling was performed to evaluate both cooling performance of conventional impingement cooling and multislot cooling when applied to a HPT nozzle. As a result it was found that the multislot cooling is well applicable to cooling of HPT airfoils.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleStudy on Advanced Internal Cooling Technologies for the Development of Next-Generation Small-Class Aircraft Engines
    typeJournal Paper
    journal volume132
    journal issue3
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.3151602
    journal fristpage31019
    identifier eissn1528-8900
    keywordsCooling
    keywordsPressure AND Nozzles
    treeJournal of Turbomachinery:;2010:;volume( 132 ):;issue: 003
    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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