Computational design and experimental evaluation of using a leading edge fillet on a gas turbine vane

G. A. Zess, Karen Ann Thole

    Research output: Contribution to journalArticle

    99 Citations (Scopus)

    Abstract

    With the desire for increased power output for a gas turbine engine comes the continual push to achieve higher turbine inlet temperatures. Higher temperatures result in large thermal and mechanical stresses particularly along the nozzle guide vane. One critical region along a vane is the leading edge-endwall juncture. Based on the assumption that the approaching flow to this juncture is similar to a two-dimensional boundary layer, previous studies have shown that a horseshoe vortex forms. This vortex forms because of a radial total pressure gradient from the approaching boundary layer. This paper documents the computational design and experimental validation of a fillet placed at the leading edge-endwall juncture of a guide vane to eliminate the horseshoe vortex. The fillet design effectively accelerated the incoming boundary layer thereby mitigating the effect of the total pressure gradient. To verify the CFD studies used to design the leading edge fillet, flowfield measurements were performed in a large-scale, linear, vane cascade. The flowfield measurements were performed with a laser Doppler velocimeter in four planes orientated orthogonal to the vane. Good agreement between the CFD predictions and the experimental measurements verified the effectiveness of the leading edge fillet at eliminating the horseshoe vortex. The flow-field results showed that the turbulent kinetic energy levels were significantly reduced in the endwall region because of the absence of the unsteady horseshoe vortex.

    Original languageEnglish (US)
    Pages (from-to)167-175
    Number of pages9
    JournalJournal of Turbomachinery
    Volume124
    Issue number2
    DOIs
    StatePublished - Apr 1 2002

    Fingerprint

    Gas turbines
    Vortex flow
    Boundary layers
    Pressure gradient
    Computational fluid dynamics
    Turbines
    Laser Doppler velocimeters
    Kinetic energy
    Electron energy levels
    Nozzles
    Flow fields
    Temperature

    All Science Journal Classification (ASJC) codes

    • Mechanical Engineering

    Cite this

    @article{cb372599e22e439a82770b303a985b2f,
    title = "Computational design and experimental evaluation of using a leading edge fillet on a gas turbine vane",
    abstract = "With the desire for increased power output for a gas turbine engine comes the continual push to achieve higher turbine inlet temperatures. Higher temperatures result in large thermal and mechanical stresses particularly along the nozzle guide vane. One critical region along a vane is the leading edge-endwall juncture. Based on the assumption that the approaching flow to this juncture is similar to a two-dimensional boundary layer, previous studies have shown that a horseshoe vortex forms. This vortex forms because of a radial total pressure gradient from the approaching boundary layer. This paper documents the computational design and experimental validation of a fillet placed at the leading edge-endwall juncture of a guide vane to eliminate the horseshoe vortex. The fillet design effectively accelerated the incoming boundary layer thereby mitigating the effect of the total pressure gradient. To verify the CFD studies used to design the leading edge fillet, flowfield measurements were performed in a large-scale, linear, vane cascade. The flowfield measurements were performed with a laser Doppler velocimeter in four planes orientated orthogonal to the vane. Good agreement between the CFD predictions and the experimental measurements verified the effectiveness of the leading edge fillet at eliminating the horseshoe vortex. The flow-field results showed that the turbulent kinetic energy levels were significantly reduced in the endwall region because of the absence of the unsteady horseshoe vortex.",
    author = "Zess, {G. A.} and Thole, {Karen Ann}",
    year = "2002",
    month = "4",
    day = "1",
    doi = "10.1115/1.1460914",
    language = "English (US)",
    volume = "124",
    pages = "167--175",
    journal = "Journal of Turbomachinery",
    issn = "0889-504X",
    publisher = "American Society of Mechanical Engineers(ASME)",
    number = "2",

    }

    Computational design and experimental evaluation of using a leading edge fillet on a gas turbine vane. / Zess, G. A.; Thole, Karen Ann.

    In: Journal of Turbomachinery, Vol. 124, No. 2, 01.04.2002, p. 167-175.

    Research output: Contribution to journalArticle

    TY - JOUR

    T1 - Computational design and experimental evaluation of using a leading edge fillet on a gas turbine vane

    AU - Zess, G. A.

    AU - Thole, Karen Ann

    PY - 2002/4/1

    Y1 - 2002/4/1

    N2 - With the desire for increased power output for a gas turbine engine comes the continual push to achieve higher turbine inlet temperatures. Higher temperatures result in large thermal and mechanical stresses particularly along the nozzle guide vane. One critical region along a vane is the leading edge-endwall juncture. Based on the assumption that the approaching flow to this juncture is similar to a two-dimensional boundary layer, previous studies have shown that a horseshoe vortex forms. This vortex forms because of a radial total pressure gradient from the approaching boundary layer. This paper documents the computational design and experimental validation of a fillet placed at the leading edge-endwall juncture of a guide vane to eliminate the horseshoe vortex. The fillet design effectively accelerated the incoming boundary layer thereby mitigating the effect of the total pressure gradient. To verify the CFD studies used to design the leading edge fillet, flowfield measurements were performed in a large-scale, linear, vane cascade. The flowfield measurements were performed with a laser Doppler velocimeter in four planes orientated orthogonal to the vane. Good agreement between the CFD predictions and the experimental measurements verified the effectiveness of the leading edge fillet at eliminating the horseshoe vortex. The flow-field results showed that the turbulent kinetic energy levels were significantly reduced in the endwall region because of the absence of the unsteady horseshoe vortex.

    AB - With the desire for increased power output for a gas turbine engine comes the continual push to achieve higher turbine inlet temperatures. Higher temperatures result in large thermal and mechanical stresses particularly along the nozzle guide vane. One critical region along a vane is the leading edge-endwall juncture. Based on the assumption that the approaching flow to this juncture is similar to a two-dimensional boundary layer, previous studies have shown that a horseshoe vortex forms. This vortex forms because of a radial total pressure gradient from the approaching boundary layer. This paper documents the computational design and experimental validation of a fillet placed at the leading edge-endwall juncture of a guide vane to eliminate the horseshoe vortex. The fillet design effectively accelerated the incoming boundary layer thereby mitigating the effect of the total pressure gradient. To verify the CFD studies used to design the leading edge fillet, flowfield measurements were performed in a large-scale, linear, vane cascade. The flowfield measurements were performed with a laser Doppler velocimeter in four planes orientated orthogonal to the vane. Good agreement between the CFD predictions and the experimental measurements verified the effectiveness of the leading edge fillet at eliminating the horseshoe vortex. The flow-field results showed that the turbulent kinetic energy levels were significantly reduced in the endwall region because of the absence of the unsteady horseshoe vortex.

    UR - http://www.scopus.com/inward/record.url?scp=0036541928&partnerID=8YFLogxK

    UR - http://www.scopus.com/inward/citedby.url?scp=0036541928&partnerID=8YFLogxK

    U2 - 10.1115/1.1460914

    DO - 10.1115/1.1460914

    M3 - Article

    VL - 124

    SP - 167

    EP - 175

    JO - Journal of Turbomachinery

    JF - Journal of Turbomachinery

    SN - 0889-504X

    IS - 2

    ER -