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    Use of an Immersed Mesh for High Resolution Modeling of Film Cooling Flows

    Source: Journal of Turbomachinery:;2013:;volume( 135 ):;issue: 001::page 11022
    Author:
    Lad, B.
    ,
    He, L.
    DOI: 10.1115/1.4006398
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The development of a high pressure turbine requires the accurate prediction of flow within and around film cooling holes. However, the length scales inherent to film cooling flows produce a large disparity against those of the mainstream flow; hence they cannot be resolved by a mesh generated for an aerodynamics analysis. Furthermore, the process of meshing cooling holes is not only time consuming but cumbersome; thus making the parametric study of film cooling effectiveness for a given blade geometry, using hole geometry and distribution, very difficult in a design environment. In this paper an immersed mesh block (IMB) approach is proposed which allows the refined mesh of a cooling hole to be immersed into the coarser mesh of a nozzle guide vane (NGV) and solved simultaneously while maintaining mass conservation. By employing twoway coupling, the flow physics in and around cooling holes is able to interact with the mainstream; hence the length scales of both types of flow are appropriately resolved. A generic cooling hole design can then be mapped to a given aerofoil geometry multiple times to achieve an appropriate distribution of cooling holes. The results show that for a realistic transonic blade, a configuration consisting of up to 200 cooling holes can be efficiently and accurately calculated—while retaining the original aerodynamic mesh but with a much enhanced resolution for the film cooling.
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      Use of an Immersed Mesh for High Resolution Modeling of Film Cooling Flows

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    contributor authorLad, B.
    contributor authorHe, L.
    date accessioned2017-05-09T01:03:19Z
    date available2017-05-09T01:03:19Z
    date issued2013
    identifier issn0889-504X
    identifier otherturb_135_1_011022.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/153383
    description abstractThe development of a high pressure turbine requires the accurate prediction of flow within and around film cooling holes. However, the length scales inherent to film cooling flows produce a large disparity against those of the mainstream flow; hence they cannot be resolved by a mesh generated for an aerodynamics analysis. Furthermore, the process of meshing cooling holes is not only time consuming but cumbersome; thus making the parametric study of film cooling effectiveness for a given blade geometry, using hole geometry and distribution, very difficult in a design environment. In this paper an immersed mesh block (IMB) approach is proposed which allows the refined mesh of a cooling hole to be immersed into the coarser mesh of a nozzle guide vane (NGV) and solved simultaneously while maintaining mass conservation. By employing twoway coupling, the flow physics in and around cooling holes is able to interact with the mainstream; hence the length scales of both types of flow are appropriately resolved. A generic cooling hole design can then be mapped to a given aerofoil geometry multiple times to achieve an appropriate distribution of cooling holes. The results show that for a realistic transonic blade, a configuration consisting of up to 200 cooling holes can be efficiently and accurately calculated—while retaining the original aerodynamic mesh but with a much enhanced resolution for the film cooling.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleUse of an Immersed Mesh for High Resolution Modeling of Film Cooling Flows
    typeJournal Paper
    journal volume135
    journal issue1
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.4006398
    journal fristpage11022
    journal lastpage11022
    identifier eissn1528-8900
    treeJournal of Turbomachinery:;2013:;volume( 135 ):;issue: 001
    contenttypeFulltext
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