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    Film Cooling Performance on a Turbine Blade With Subregional Compound Angle

    Source: ASME Journal of Heat and Mass Transfer:;2024:;volume( 146 ):;issue: 005::page 53801-1
    Author:
    Li, Guoqing
    ,
    Li, Ang
    ,
    Zhang, Shen
    ,
    Wang, Chenfeng
    ,
    Lu, Xingen
    DOI: 10.1115/1.4064153
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Under the influence of secondary flow, the film cooling deviates from the flow direction on the turbine blade, which directly results in undesirable uneven film coverage. On the pressure side, the film appears divergent, while on the suction side, it is bunched. To solve this problem, a kind of subregional compound angle is proposed, in which the angle in the spanwise direction is different in different regions depending on the strength and direction of the secondary flow. Four rows of film holes with five kinds of subregional compound angles are provided on the pressure side, while two rows of film holes with different subregional compound angles are provided on the suction side. The Reynolds Average Navier–Stokes (RANS) method of the SST k–ω turbulence model is chosen to solve the above blade arrangement. The results show that a significant improvement can be achieved by the introducing subregional compound injection of the film coolant compared to the case of simple injection. In compound injection, the injectant maintains sufficient momentum to prevent the coolant from being swept away by the secondary flow. This was found to be largely the case for most holes on the pressure side, and some holes on the suction side. However, for holes near the downstream section of the suction surface of the blade, where the passage vortex is strongest, no value is found for the compound angle that could redirect the coolant along the blade profile without radial deviation. In some cases, excessive values of the compound angle led to jet liftoff rather than spreading the film along the surface.
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      Film Cooling Performance on a Turbine Blade With Subregional Compound Angle

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    contributor authorLi, Guoqing
    contributor authorLi, Ang
    contributor authorZhang, Shen
    contributor authorWang, Chenfeng
    contributor authorLu, Xingen
    date accessioned2024-04-24T22:29:09Z
    date available2024-04-24T22:29:09Z
    date copyright3/4/2024 12:00:00 AM
    date issued2024
    identifier issn2832-8450
    identifier otherht_146_05_053801.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4295310
    description abstractUnder the influence of secondary flow, the film cooling deviates from the flow direction on the turbine blade, which directly results in undesirable uneven film coverage. On the pressure side, the film appears divergent, while on the suction side, it is bunched. To solve this problem, a kind of subregional compound angle is proposed, in which the angle in the spanwise direction is different in different regions depending on the strength and direction of the secondary flow. Four rows of film holes with five kinds of subregional compound angles are provided on the pressure side, while two rows of film holes with different subregional compound angles are provided on the suction side. The Reynolds Average Navier–Stokes (RANS) method of the SST k–ω turbulence model is chosen to solve the above blade arrangement. The results show that a significant improvement can be achieved by the introducing subregional compound injection of the film coolant compared to the case of simple injection. In compound injection, the injectant maintains sufficient momentum to prevent the coolant from being swept away by the secondary flow. This was found to be largely the case for most holes on the pressure side, and some holes on the suction side. However, for holes near the downstream section of the suction surface of the blade, where the passage vortex is strongest, no value is found for the compound angle that could redirect the coolant along the blade profile without radial deviation. In some cases, excessive values of the compound angle led to jet liftoff rather than spreading the film along the surface.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleFilm Cooling Performance on a Turbine Blade With Subregional Compound Angle
    typeJournal Paper
    journal volume146
    journal issue5
    journal titleASME Journal of Heat and Mass Transfer
    identifier doi10.1115/1.4064153
    journal fristpage53801-1
    journal lastpage53801-15
    page15
    treeASME Journal of Heat and Mass Transfer:;2024:;volume( 146 ):;issue: 005
    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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