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    Tail-Integrated Boundary Layer Ingesting Propulsion Systems for Turbo-Electric Aircraft

    Source: Journal of Turbomachinery:;2023:;volume( 146 ):;issue: 002::page 21004-1
    Author:
    Chen, Zhibo
    ,
    Galbraith, Marshall C.
    ,
    Spakovszky, Zoltán S.
    ,
    Greitzer, Edward M.
    ,
    Sabnis, Jayant S.
    DOI: 10.1115/1.4063930
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: This article presents conceptual design guidelines and results for a tail-integrated propulsion system for a turbo-electric civil transport aircraft with boundary layer ingestion (BLI). The aerodynamic performance goal is separation-free and shock-free operation at cruise with fuel burn reduction, compared with a baseline conventional aircraft for the same mission. The assessment of BLI benefits is based on calculations using CFD and TASOPT software, both to characterize the design challenges and to establish the physical mechanisms for resolving these challenges. The guidelines include a “horseshoe” inlet to accept the non-uniform flow without incurring separation, a nacelle profile similar to supercritical airfoils to reduce shock strength, and an annular nozzle to eliminate flow separation between tail-BLI propulsors. The conceptual design has nine BLI propulsors with electric fans on an axisymmetric tail of a single-aisle aircraft. The fans are powered by twin underwing turbofans. The estimated benefit of the tail-BLI, twin underwing turbofan aircraft is 10.4% in Payload-Range Fuel Consumption (PRFC) at a cruise Mach number of 0.8, compared to a baseline twin underwing turbofan configuration. Sensitivity studies further show that a 1% increase in installed (i.e., with BLI) fan isentropic efficiency translates to 0.8% rise in PRFC benefit.
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      Tail-Integrated Boundary Layer Ingesting Propulsion Systems for Turbo-Electric Aircraft

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    http://yetl.yabesh.ir/yetl1/handle/yetl/4295937
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    • Journal of Turbomachinery

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    contributor authorChen, Zhibo
    contributor authorGalbraith, Marshall C.
    contributor authorSpakovszky, Zoltán S.
    contributor authorGreitzer, Edward M.
    contributor authorSabnis, Jayant S.
    date accessioned2024-04-24T22:49:25Z
    date available2024-04-24T22:49:25Z
    date copyright11/8/2023 12:00:00 AM
    date issued2023
    identifier issn0889-504X
    identifier otherturbo_146_2_021004.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4295937
    description abstractThis article presents conceptual design guidelines and results for a tail-integrated propulsion system for a turbo-electric civil transport aircraft with boundary layer ingestion (BLI). The aerodynamic performance goal is separation-free and shock-free operation at cruise with fuel burn reduction, compared with a baseline conventional aircraft for the same mission. The assessment of BLI benefits is based on calculations using CFD and TASOPT software, both to characterize the design challenges and to establish the physical mechanisms for resolving these challenges. The guidelines include a “horseshoe” inlet to accept the non-uniform flow without incurring separation, a nacelle profile similar to supercritical airfoils to reduce shock strength, and an annular nozzle to eliminate flow separation between tail-BLI propulsors. The conceptual design has nine BLI propulsors with electric fans on an axisymmetric tail of a single-aisle aircraft. The fans are powered by twin underwing turbofans. The estimated benefit of the tail-BLI, twin underwing turbofan aircraft is 10.4% in Payload-Range Fuel Consumption (PRFC) at a cruise Mach number of 0.8, compared to a baseline twin underwing turbofan configuration. Sensitivity studies further show that a 1% increase in installed (i.e., with BLI) fan isentropic efficiency translates to 0.8% rise in PRFC benefit.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleTail-Integrated Boundary Layer Ingesting Propulsion Systems for Turbo-Electric Aircraft
    typeJournal Paper
    journal volume146
    journal issue2
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.4063930
    journal fristpage21004-1
    journal lastpage21004-10
    page10
    treeJournal of Turbomachinery:;2023:;volume( 146 ):;issue: 002
    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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