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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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Numerical investigation of adiabatic film cooling effectiveness through compound angle variations
, 2020Provided are numerically predicted distributions of film cooling effectiveness for single cylinder film holes and for single 15° forward diffused film cooling holes, with compound angles ranging from 0° to 180°.
S. Tamang +6 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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Journal of turbomachinery, 2018
Internal coolant passages of gas turbine vanes and blades have various orientations relative to the external hot gas flow. As a consequence, the inflow of film cooling holes varies as well.
M. Fraas +3 more
semanticscholar +1 more source
Internal coolant passages of gas turbine vanes and blades have various orientations relative to the external hot gas flow. As a consequence, the inflow of film cooling holes varies as well.
M. Fraas +3 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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Effect of Film Cooling Hole Area Ratio on Adiabatic Film Cooling Effectiveness Over a Flat Plate
ASME 2013 Gas Turbine India Conference, 2013In the present study the film cooling performance is analyzed for a flat plate model with different hole area ratios. Here “Area Ratio” is defined as the ratio between the cross sectional area of the hole at inlet to the exit of the hole. The area ratios which are considered for analyzing are 1, 2 and 3.
J. Felix +4 more
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Journal of turbomachinery, 2019
This study is concerned with the film cooling effectiveness of the flow issuing from the gap between the nozzle guide vane (NGV) and the transition duct on the NGV endwall, i.e., the purge slot.
G. Müller +3 more
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This study is concerned with the film cooling effectiveness of the flow issuing from the gap between the nozzle guide vane (NGV) and the transition duct on the NGV endwall, i.e., the purge slot.
G. Müller +3 more
semanticscholar +1 more source
On the Film Cooling Effectiveness Controversy
Volume 1A: Gas Turbines, 1979A relationship between isothermal and adiabatic film cooling effectiveness has been derived. Data from the open literature have been used to validate this relationship. This effectively uncouples short duration techniques from the concept of isothermal effectiveness.
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The effect of unsteadiness on film cooling effectiveness
33rd Aerospace Sciences Meeting and Exhibit, 1995Abstract : A unique feature of turbine rotor blade film cooling is the main flow unsteadiness caused by the upstream stator vanes. The combined effect of the vane inviscid flow field and the trailing edge wake results in a rapidly changing external pressure at the film cooled blade surface.
Jeffrey Bons +4 more
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