YaBeSH Engineering and Technology Library

    • Journals
    • PaperQuest
    • YSE Standards
    • YaBeSH
    • Login
    View Item 
    •   YE&T Library
    • ASME
    • Journal of Engineering for Gas Turbines and Power
    • View Item
    •   YE&T Library
    • ASME
    • Journal of Engineering for Gas Turbines and Power
    • View Item
    • All Fields
    • Source Title
    • Year
    • Publisher
    • Title
    • Subject
    • Author
    • DOI
    • ISBN
    Advanced Search
    JavaScript is disabled for your browser. Some features of this site may not work without it.

    Archive

    Blackbox Optimization for Aircraft Engine Blades With Contact Interfaces

    Source: Journal of Engineering for Gas Turbines and Power:;2019:;volume( 141 ):;issue: 006::page 61016
    Author:
    Lainé, Julien
    ,
    Piollet, Elsa
    ,
    Nyssen, Florence
    ,
    Batailly, Alain
    DOI: 10.1115/1.4042808
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: In modern aircraft engines, reduced operating clearances between rotating blade tips and the surrounding casing increase the risk of blade/casing structural contacts, which may lead to high blade vibration levels. Therefore, structural contacts must now be accounted for as early as in the engine design stage. As the vibrations resulting from contact are intrinsically nonlinear, direct optimization of blade shapes based on vibration simulation is not realistic in an industrial context. A recent study on a blade featuring significantly lower vibration levels following contact event identified a potential criterion to estimate a blade sensitivity to contact interactions. This criterion is based on the notion of dynamic clearance, a quantity describing the evolution of the blade/casing clearance as the blade vibrates along one of its free-vibration modes. This paper presents an optimization procedure, which minimizes the dynamic clearance as a first step toward the integration of structural criteria in blade design. A dedicated blade geometry parameterization is introduced to allow for an efficient optimization of the blade shape. The optimization procedure is applied to the three-dimensional (3D) properties of two different blades. In both cases, initial and optimized blades are compared by means of an in-house numerical tool dedicated to the simulation of structural contact events with a surrounding casing. The simulations focus on rubbing phenomena, involving the vibration of a single blade. Simulation results show a significant reduction of vibration levels following contact interactions for the optimized blades. Critical speeds related to the mode on which the dynamic clearance is computed are successfully eliminated by the blade shape optimization. For the investigated blade geometries, backward sweep and backward lean angles are associated with reduced contact interactions compared to forward sweep and forward lean angles.
    • Download: (5.715Mb)
    • Show Full MetaData Hide Full MetaData
    • Get RIS
    • Item Order
    • Go To Publisher
    • Price: 5000 Rial
    • Statistics

      Blackbox Optimization for Aircraft Engine Blades With Contact Interfaces

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/4255976
    Collections
    • Journal of Engineering for Gas Turbines and Power

    Show full item record

    contributor authorLainé, Julien
    contributor authorPiollet, Elsa
    contributor authorNyssen, Florence
    contributor authorBatailly, Alain
    date accessioned2019-03-17T10:10:49Z
    date available2019-03-17T10:10:49Z
    date copyright2/25/2019 12:00:00 AM
    date issued2019
    identifier issn0742-4795
    identifier othergtp_141_06_061016.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4255976
    description abstractIn modern aircraft engines, reduced operating clearances between rotating blade tips and the surrounding casing increase the risk of blade/casing structural contacts, which may lead to high blade vibration levels. Therefore, structural contacts must now be accounted for as early as in the engine design stage. As the vibrations resulting from contact are intrinsically nonlinear, direct optimization of blade shapes based on vibration simulation is not realistic in an industrial context. A recent study on a blade featuring significantly lower vibration levels following contact event identified a potential criterion to estimate a blade sensitivity to contact interactions. This criterion is based on the notion of dynamic clearance, a quantity describing the evolution of the blade/casing clearance as the blade vibrates along one of its free-vibration modes. This paper presents an optimization procedure, which minimizes the dynamic clearance as a first step toward the integration of structural criteria in blade design. A dedicated blade geometry parameterization is introduced to allow for an efficient optimization of the blade shape. The optimization procedure is applied to the three-dimensional (3D) properties of two different blades. In both cases, initial and optimized blades are compared by means of an in-house numerical tool dedicated to the simulation of structural contact events with a surrounding casing. The simulations focus on rubbing phenomena, involving the vibration of a single blade. Simulation results show a significant reduction of vibration levels following contact interactions for the optimized blades. Critical speeds related to the mode on which the dynamic clearance is computed are successfully eliminated by the blade shape optimization. For the investigated blade geometries, backward sweep and backward lean angles are associated with reduced contact interactions compared to forward sweep and forward lean angles.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleBlackbox Optimization for Aircraft Engine Blades With Contact Interfaces
    typeJournal Paper
    journal volume141
    journal issue6
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.4042808
    journal fristpage61016
    journal lastpage061016-16
    treeJournal of Engineering for Gas Turbines and Power:;2019:;volume( 141 ):;issue: 006
    contenttypeFulltext
    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
    yabeshDSpacePersian
     
    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
    yabeshDSpacePersian