Results 71 to 80 of about 315 (116)
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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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Adiabatic Film Cooling Effectiveness Measurements Throughout Multirow Film Cooling Arrays
Journal of Turbomachinery, 2017Adiabatic film cooling effectiveness measurements are obtained using pressure-sensitive paint (PSP) on a flat film cooled surface. The effects of blowing ratio and hole spacing are investigated for four multirow arrays comprised of eight rows containing 52 holes of 3.8 mm diameter with 20 deg inclination angles and hole length-to-diameter ratio of 11.2.
Natsui, Greg +3 more
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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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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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The Effect of High Free-Stream Turbulence on Film Cooling Effectiveness
Journal of Turbomachinery, 1994This study investigated the adiabatic wall cooling effectiveness of a single row of film cooling holes injecting into a turbulent flat plate boundary layer below a turbulent, zero pressure gradient free stream. Levels of free-stream turbulence (Tu) up to 17.4 percent were generated using a method that simulates conditions at a gas turbine combustor ...
Jeffrey P. Bons +2 more
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Film Cooling Effectiveness and Flow Structures of Butterfly-Shaped Film Cooling Hole Configuration
Volume 7A: Heat Transfer — Combustors; Film Cooling, 2023Abstract Film cooling is applied to various high-temperature components of a gas turbine and greatly affected by the shape of the injection hole. Numerous studies have been conducted to investigate various film cooling structures to increase the film cooling effectiveness by inducing coolants toward the surface.
Jin Young Jeong +4 more
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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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Effect of Vortex Generators on Film Cooling Effectiveness
Journal of Turbomachinery, 2015Film cooling is often adopted, where coolant jets are ejected to form a protective layer on the surface against the hot combustor gases. The bending of jets in crossflow results in counter rotating vortex pair (CRVP), which is a cause for high jet lift-off and poor film cooling effectiveness in the near field.
S. Sarkar, Ganesh Ranakoti
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Effect of Stagnation Regions on Film Cooling Effectiveness
Volume 4: Turbo Expo 2007, Parts A and B, 2007Over the last decades, researchers have investigated many aspects of film cooling. The present study investigates the impact of stagnation region created by a downstream airfoil on endwall film cooling effectiveness. Experimental measurements are presented for a single row of cylindrical holes inclined at 35° with hole length to diameter ratio, L/D = 7.
RodrÃguez, S. +4 more
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