Transonic film-cooling investigations

effects of hole shapes and orientations

S. Wittig, A. Schulz, M. Gritsch, Karen Ann Thole

    Research output: Contribution to journalArticle

    35 Citations (Scopus)

    Abstract

    The emphasis of the present study is to understand the effects of various flowfield and geometrical parameters in the nearfield region of a scaled-up film-cooling hole on a flat test plate. The effect of these different parameters on adiabatic wall effectiveness, heat transfer coefficients, discharge coefficients and the near-hole velocity field will be addressed. The geometrical parameters of concern include several angles of inclination and rotation of a cylindrical film-cooling hole and two different hole shapes - a fanshaped hole and a laidback fanshaped hole. The fluid dynamic parameters include both the internal and external Mach number as well as the mainstream-to-coolant ratios of total temperature, velocity, mass flux, and momentum flux. In particular, the interaction of a film-cooling jet being injected into a transonic mainstream will be studied. This paper includes a detailed description of the test rig design as well as the measuring techniques. Firstly, tests revealing the operability of the test rig will be discussed. Finally, an outlook of the comprehensive experimental and numerical program will be given.

    Original languageEnglish (US)
    Journal[No source information available]
    StatePublished - 1996

    Fingerprint

    Cooling
    Fluid dynamics
    Coolants
    Heat transfer coefficients
    Mach number
    Momentum
    Mass transfer
    Fluxes
    Temperature

    All Science Journal Classification (ASJC) codes

    • Mechanical Engineering

    Cite this

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    abstract = "The emphasis of the present study is to understand the effects of various flowfield and geometrical parameters in the nearfield region of a scaled-up film-cooling hole on a flat test plate. The effect of these different parameters on adiabatic wall effectiveness, heat transfer coefficients, discharge coefficients and the near-hole velocity field will be addressed. The geometrical parameters of concern include several angles of inclination and rotation of a cylindrical film-cooling hole and two different hole shapes - a fanshaped hole and a laidback fanshaped hole. The fluid dynamic parameters include both the internal and external Mach number as well as the mainstream-to-coolant ratios of total temperature, velocity, mass flux, and momentum flux. In particular, the interaction of a film-cooling jet being injected into a transonic mainstream will be studied. This paper includes a detailed description of the test rig design as well as the measuring techniques. Firstly, tests revealing the operability of the test rig will be discussed. Finally, an outlook of the comprehensive experimental and numerical program will be given.",
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    Transonic film-cooling investigations : effects of hole shapes and orientations. / Wittig, S.; Schulz, A.; Gritsch, M.; Thole, Karen Ann.

    In: [No source information available], 1996.

    Research output: Contribution to journalArticle

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    T1 - Transonic film-cooling investigations

    T2 - effects of hole shapes and orientations

    AU - Wittig, S.

    AU - Schulz, A.

    AU - Gritsch, M.

    AU - Thole, Karen Ann

    PY - 1996

    Y1 - 1996

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    AB - The emphasis of the present study is to understand the effects of various flowfield and geometrical parameters in the nearfield region of a scaled-up film-cooling hole on a flat test plate. The effect of these different parameters on adiabatic wall effectiveness, heat transfer coefficients, discharge coefficients and the near-hole velocity field will be addressed. The geometrical parameters of concern include several angles of inclination and rotation of a cylindrical film-cooling hole and two different hole shapes - a fanshaped hole and a laidback fanshaped hole. The fluid dynamic parameters include both the internal and external Mach number as well as the mainstream-to-coolant ratios of total temperature, velocity, mass flux, and momentum flux. In particular, the interaction of a film-cooling jet being injected into a transonic mainstream will be studied. This paper includes a detailed description of the test rig design as well as the measuring techniques. Firstly, tests revealing the operability of the test rig will be discussed. Finally, an outlook of the comprehensive experimental and numerical program will be given.

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