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    Investigations on the Effects of Inflow Condition and Tip Clearance Size to the Performance of a Compressor Rotor

    Source: Journal of Engineering for Gas Turbines and Power:;2014:;volume( 136 ):;issue: 012::page 122608
    Author:
    Zhang, Chenkai
    ,
    Hu, Jun
    ,
    Wang, Zhiqiang
    DOI: 10.1115/1.4027906
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: To clearly clarify the effects of different upstream boundary layer thickness and tip clearance size to the detailed tip flow field and flow mechanism, numerical simulations are performed on a subsonic compressor rotor, which is used for lowspeed model testing of a rear stage embedded in a modern highpressure compressor. First, available experimental data are adopted to validate the numerical method. Second, comparisons are made for tip leakage vortex (TLV) structure, the interface of leakage flow/mainflow, endwall loss, isentropic efficiency and pressurerise among different operating conditions. Then, effects of different clearance sizes and inflow boundary layer thicknesses are investigated. Finally, the selfinduced unsteadiness at one nearstall (NS) operating condition is studied for different cases. Results show that the increment of tip clearance size has a deleterious effect on rotor efficiency and pressurerise performance over the whole operating range, while thickening the inflow boundary layer is almost the same except that its pressurerise performance will be increased at mass flow rate larger than design operating condition. Selfinduced unsteadiness occurs at NS operating conditions, and its appearance largely depends on tip clearance size, while the effect of upstream boundary layer thickness is little.
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      Investigations on the Effects of Inflow Condition and Tip Clearance Size to the Performance of a Compressor Rotor

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    http://yetl.yabesh.ir/yetl1/handle/yetl/154878
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    • Journal of Engineering for Gas Turbines and Power

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    contributor authorZhang, Chenkai
    contributor authorHu, Jun
    contributor authorWang, Zhiqiang
    date accessioned2017-05-09T01:08:13Z
    date available2017-05-09T01:08:13Z
    date issued2014
    identifier issn1528-8919
    identifier othergtp_136_12_122608.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/154878
    description abstractTo clearly clarify the effects of different upstream boundary layer thickness and tip clearance size to the detailed tip flow field and flow mechanism, numerical simulations are performed on a subsonic compressor rotor, which is used for lowspeed model testing of a rear stage embedded in a modern highpressure compressor. First, available experimental data are adopted to validate the numerical method. Second, comparisons are made for tip leakage vortex (TLV) structure, the interface of leakage flow/mainflow, endwall loss, isentropic efficiency and pressurerise among different operating conditions. Then, effects of different clearance sizes and inflow boundary layer thicknesses are investigated. Finally, the selfinduced unsteadiness at one nearstall (NS) operating condition is studied for different cases. Results show that the increment of tip clearance size has a deleterious effect on rotor efficiency and pressurerise performance over the whole operating range, while thickening the inflow boundary layer is almost the same except that its pressurerise performance will be increased at mass flow rate larger than design operating condition. Selfinduced unsteadiness occurs at NS operating conditions, and its appearance largely depends on tip clearance size, while the effect of upstream boundary layer thickness is little.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleInvestigations on the Effects of Inflow Condition and Tip Clearance Size to the Performance of a Compressor Rotor
    typeJournal Paper
    journal volume136
    journal issue12
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.4027906
    journal fristpage122608
    journal lastpage122608
    identifier eissn0742-4795
    treeJournal of Engineering for Gas Turbines and Power:;2014:;volume( 136 ):;issue: 012
    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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