Friction damping of flutter in gas turbine engines.

    Research output: Contribution to journalArticle

    Abstract

    The physical concepts and mathematical techniques needed to examine the effects of friction dampers on gas turbine engine rotor stages are developed. Blade to ground dampers are studied using a single degree of freedom model of an isolated blade. The range of conditions for stable response, maximum stabilized negative damping, optimum damper parameters and the effect of external excitation are also examined. The use of friction dampers in three, six, nine and twelve bladed disks is considered.

    Original languageEnglish (US)
    Journal[No source information available]
    StatePublished - Jan 1 1983

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    gas turbine engines
    flutter
    dampers
    Gas turbines
    Turbines
    friction
    Damping
    damping
    Friction
    blades
    Turbomachine blades
    Rotors
    rotors
    degrees of freedom
    excitation

    All Science Journal Classification (ASJC) codes

    • Engineering(all)

    Cite this

    @article{2565512aa61840ebbe7e2fef440fa51b,
    title = "Friction damping of flutter in gas turbine engines.",
    abstract = "The physical concepts and mathematical techniques needed to examine the effects of friction dampers on gas turbine engine rotor stages are developed. Blade to ground dampers are studied using a single degree of freedom model of an isolated blade. The range of conditions for stable response, maximum stabilized negative damping, optimum damper parameters and the effect of external excitation are also examined. The use of friction dampers in three, six, nine and twelve bladed disks is considered.",
    author = "Alok Sinha",
    year = "1983",
    month = "1",
    day = "1",
    language = "English (US)",
    journal = "Journal of Fluid Mechanics",
    issn = "0022-1120",
    publisher = "Cambridge University Press",

    }

    Friction damping of flutter in gas turbine engines. / Sinha, Alok.

    In: [No source information available], 01.01.1983.

    Research output: Contribution to journalArticle

    TY - JOUR

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    AU - Sinha, Alok

    PY - 1983/1/1

    Y1 - 1983/1/1

    N2 - The physical concepts and mathematical techniques needed to examine the effects of friction dampers on gas turbine engine rotor stages are developed. Blade to ground dampers are studied using a single degree of freedom model of an isolated blade. The range of conditions for stable response, maximum stabilized negative damping, optimum damper parameters and the effect of external excitation are also examined. The use of friction dampers in three, six, nine and twelve bladed disks is considered.

    AB - The physical concepts and mathematical techniques needed to examine the effects of friction dampers on gas turbine engine rotor stages are developed. Blade to ground dampers are studied using a single degree of freedom model of an isolated blade. The range of conditions for stable response, maximum stabilized negative damping, optimum damper parameters and the effect of external excitation are also examined. The use of friction dampers in three, six, nine and twelve bladed disks is considered.

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