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    Determination of Cooling Parameters for a High-Speed, True-Scale, Metallic Turbine Vane

    Source: Journal of Turbomachinery:;2017:;volume( 139 ):;issue: 001::page 11001
    Author:
    Polanka, Marc D.
    ,
    Rutledge, James L.
    ,
    Bogard, David G.
    ,
    Anthony, Richard J.
    DOI: 10.1115/1.4033974
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Facilities such as the Turbine Research Facility (TRF) at the Air Force Research Laboratory have been acquiring uncooled heat transfer measurements on full-scale metallic airfoils for several years. The addition of cooling flow to this type of facility has provided new capabilities and new challenges. Two primary challenges for cooled rotating hardware are that the true local film temperature is unknown, and cooled thin-walled metallic airfoils prohibit semi-infinite heat conduction calculation. Extracting true local adiabatic effectiveness and the heat transfer coefficient from measurements of surface temperature and surface heat transfer is therefore difficult. In contrast, another cooling parameter, the overall effectiveness (ϕ), is readily obtained from the measurements of surface temperature, internal coolant temperature, and mainstream temperature. The overall effectiveness is a normalized measure of surface temperatures expected for actual operating conditions and is thus an important parameter that drives the life expectancy of a turbine component. Another issue is that scaling ϕ from experimental conditions to engine conditions is dependent on the heat transfer through the part. It has been well-established that the Biot number must be matched for the experimentally measured ϕ to match ϕ at engine conditions. However, the thermal conductivity of both the metal blade and the thermal barrier coating changes substantially from low-temperature to high-temperature engine conditions and usually not in the same proportion. This paper describes a novel method of replicating the correct thermal behavior of the thermal barrier coating (TBC) relative to the metal turbine while obtaining surface temperature measurements and heat fluxes. Furthermore, this paper describes how the ϕ value obtained at the low-temperature conditions can be adjusted to predict ϕ at high-temperature engine conditions when it is impossible to match the Biot number perfectly.
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      Determination of Cooling Parameters for a High-Speed, True-Scale, Metallic Turbine Vane

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    contributor authorPolanka, Marc D.
    contributor authorRutledge, James L.
    contributor authorBogard, David G.
    contributor authorAnthony, Richard J.
    date accessioned2017-11-25T07:19:46Z
    date available2017-11-25T07:19:46Z
    date copyright2016/2/8
    date issued2017
    identifier issn0889-504X
    identifier otherturbo_139_01_011001.pdf
    identifier urihttp://138.201.223.254:8080/yetl1/handle/yetl/4236001
    description abstractFacilities such as the Turbine Research Facility (TRF) at the Air Force Research Laboratory have been acquiring uncooled heat transfer measurements on full-scale metallic airfoils for several years. The addition of cooling flow to this type of facility has provided new capabilities and new challenges. Two primary challenges for cooled rotating hardware are that the true local film temperature is unknown, and cooled thin-walled metallic airfoils prohibit semi-infinite heat conduction calculation. Extracting true local adiabatic effectiveness and the heat transfer coefficient from measurements of surface temperature and surface heat transfer is therefore difficult. In contrast, another cooling parameter, the overall effectiveness (ϕ), is readily obtained from the measurements of surface temperature, internal coolant temperature, and mainstream temperature. The overall effectiveness is a normalized measure of surface temperatures expected for actual operating conditions and is thus an important parameter that drives the life expectancy of a turbine component. Another issue is that scaling ϕ from experimental conditions to engine conditions is dependent on the heat transfer through the part. It has been well-established that the Biot number must be matched for the experimentally measured ϕ to match ϕ at engine conditions. However, the thermal conductivity of both the metal blade and the thermal barrier coating changes substantially from low-temperature to high-temperature engine conditions and usually not in the same proportion. This paper describes a novel method of replicating the correct thermal behavior of the thermal barrier coating (TBC) relative to the metal turbine while obtaining surface temperature measurements and heat fluxes. Furthermore, this paper describes how the ϕ value obtained at the low-temperature conditions can be adjusted to predict ϕ at high-temperature engine conditions when it is impossible to match the Biot number perfectly.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleDetermination of Cooling Parameters for a High-Speed, True-Scale, Metallic Turbine Vane
    typeJournal Paper
    journal volume139
    journal issue1
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.4033974
    journal fristpage11001
    journal lastpage011001-9
    treeJournal of Turbomachinery:;2017:;volume( 139 ):;issue: 001
    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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