Results 171 to 180 of about 98,675 (218)
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Multihole cooling film effectiveness and heat transfer
Thermophysics and Heat Transfer Conference, 1974Adiabatic film effectiveness and heat transfer measurements with injection of secondary air through arrays of holes in a flat plate into a turbulent boundary layer are presented. Measurements were taken both within and downstream of the multihole pattern for different hole pitch-to-diameter ratios and blowing rates.
R. E. Mayle, F. J. Camarata
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Film Cooling Effectiveness and Heat Transfer of Rectangular-Shaped Film Cooling Holes
Volume 3: Turbo Expo 2002, Parts A and B, 2002An experimental study has been conducted to measure the local film-cooling effectiveness and the heat transfer coefficient for a single row of rectangular-shaped holes. The holes have a 35° inclination angle with 3 hole diameter spacing of rectangular cross-sections.
Dong Ho Rhee +2 more
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Effect of Pulsed Film Cooling on Leading Edge Film Effectiveness
Journal of Turbomachinery, 2010Detailed film effectiveness measurements have been made on a cylindrical leading edge surface for steady and pulsating flows. The film hole is off centered by 21.5 deg from the centerline and angled 20 deg to the surface and 90 deg from the streamwise direction. Two jet-to-cross-flow velocity ratios have been considered: VR=1 and 2, which correspond to
Lamyaa A. El-Gabry, Richard B. Rivir
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Effect of Rotation on Flow Field and Film Cooling Effectiveness in Film-Cooled Turbine Rotors
International Journal of Turbo & Jet-Engines, 2014AbstractExperimental and numerical investigations of flow field in a film-cooled turbine model under stationary and rotating conditions in a low-speed wind tunnel are conducted. The effects of different blowing ratios (M = 1.5, 2) on the flow field are studied.
Xiaocheng Zhu, Liangliang Liu, Feng Yuan
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Rotational effects on film cooling performance
International Journal of Numerical Methods for Heat & Fluid Flow, 2012PurposeNumerical simulations were carried out for two cooling schemes, a circular hole and a louver cooling scheme, at the leading edge of a rotor blade in a complete turbine stage.Design/methodology/approachTwo holes were positioned at the leading edge of a rotating blade, one on the pressure side and the other on the suction side. The methodology was
C.X‐Z. Zhang, I. Hassan
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Film-Cooling Effectiveness From Shaped Film Cooling Holes for a Gas Turbine Blade
Volume 4: Heat Transfer, Parts A and B, 2008The effect of film cooling holes placed along the span of a fully-cooled high pressure turbine blade in a stationary, linear cascade on film cooling effectiveness is studied using the Pressure Sensitive Paint (PSP) technique. Six rows of compound angled shaped film cooling holes are provided on the pressure side while four such rows are provided on the
Shantanu Mhetras +2 more
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Film Cooling Effectiveness for Short Film Cooling Holes Fed by a Narrow Plenum
Journal of Turbomachinery, 1999The adiabatic, steady-state liquid crystal technique was used to measure surface adiabatic film cooling effectiveness values in the near-hole region X/D<10. A parametric study was conducted for a single row of short holes L/D⩽3 fed by a narrow plenum H/D=1.
C. A. Hale +2 more
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Slot film cooling ? The effect of separation angle
Acta Mechanica, 1994Previous studies of slot film cooling have mainly concentrated on a flow geometry so arranged that the slot is flush in the containing wall. It is known that when the total pressure head of the injected flow is less than the free stream head, separation from the front of the slot is tangential to the wall (the so-called ‘lid’ effect).
Fitt, A. D., Wilmott, P.
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Volume 5A: Heat Transfer, 2017
To understand film cooling flow fields on a gas turbine blade, this paper reports a series of large-eddy simulations of an inclined round jet issuing into a crossflow. Simulations were performed at constant momentum ratio conditions, IR = 0.25, 0.5, 1.0 and Reynolds number, Re = 15,300, based on the crossflow velocity and the film cooling hole diameter.
Eiji Sakai, Toshihiko Takahashi
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To understand film cooling flow fields on a gas turbine blade, this paper reports a series of large-eddy simulations of an inclined round jet issuing into a crossflow. Simulations were performed at constant momentum ratio conditions, IR = 0.25, 0.5, 1.0 and Reynolds number, Re = 15,300, based on the crossflow velocity and the film cooling hole diameter.
Eiji Sakai, Toshihiko Takahashi
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Effects of Showerhead Cooling on Turbine Vane Suction Side Film Cooling Effectiveness
Heat Transfer: Volume 3, 2000Abstract The process of film cooling is known to severely disturb the boundary layer around a turbine airfoil. Since most film-cooled airfoils have more than one injection station, the flow field approaching a row of film cooling holes could be altered by the presence of an upstream cooling station.
Marcia I. Ethridge +2 more
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