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    Constrained Adjoint Based Aerodynamic Shape Optimization of a Single Stage Transonic Compressor

    Source: Journal of Turbomachinery:;2013:;volume( 135 ):;issue: 002::page 21017
    Author:
    Walther, Benjamin
    ,
    Nadarajah, Siva
    DOI: 10.1115/1.4007502
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: This paper develops a discrete adjoint formulation for the constrained aerodynamic shape optimization in a multistage turbomachinery environment. The adjoint approach for viscous internal flow problems and the corresponding adjoint boundary conditions are discussed. To allow for a concurrent rotor/stator optimization, a nonreflective adjoint mixingplane formulation is proposed. A sequentialquadratic programming algorithm is utilized to determine an improved airfoil shape based on the objective function gradient provided by the adjoint solution. The functionality of the proposed optimization method is demonstrated by the redesign of a midspan section of a singlestage transonic compressor. The objective is to maximize the isentropic efficiency while constraining the mass flow rate and the total pressure ratio.
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      Constrained Adjoint Based Aerodynamic Shape Optimization of a Single Stage Transonic Compressor

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    contributor authorWalther, Benjamin
    contributor authorNadarajah, Siva
    date accessioned2017-05-09T01:03:32Z
    date available2017-05-09T01:03:32Z
    date issued2013
    identifier issn0889-504X
    identifier otherturb_135_2_021017.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/153427
    description abstractThis paper develops a discrete adjoint formulation for the constrained aerodynamic shape optimization in a multistage turbomachinery environment. The adjoint approach for viscous internal flow problems and the corresponding adjoint boundary conditions are discussed. To allow for a concurrent rotor/stator optimization, a nonreflective adjoint mixingplane formulation is proposed. A sequentialquadratic programming algorithm is utilized to determine an improved airfoil shape based on the objective function gradient provided by the adjoint solution. The functionality of the proposed optimization method is demonstrated by the redesign of a midspan section of a singlestage transonic compressor. The objective is to maximize the isentropic efficiency while constraining the mass flow rate and the total pressure ratio.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleConstrained Adjoint Based Aerodynamic Shape Optimization of a Single Stage Transonic Compressor
    typeJournal Paper
    journal volume135
    journal issue2
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.4007502
    journal fristpage21017
    journal lastpage21017
    identifier eissn1528-8900
    treeJournal of Turbomachinery:;2013:;volume( 135 ):;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
    yabeshDSpacePersian