Results 171 to 180 of about 243,473 (208)
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Experimental investigations on overall cooling effect of ribbed channel with air bleeds
International Journal of Heat and Mass Transfer, 2012Abstract An experimental investigation on overall heat transfer performance of a rectangular channel, in which one wall has periodically placed oblique ribs to enhance heat exchange and cylindrical film holes to bleed cooling air, has been carried out in a hot wind tunnel at different mainstream temperatures, hot mainstream Reynolds numbers, coolant ...
Jianhua Wang +4 more
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Infrared Assessment of Overall Effectiveness of a Modern Turbine Vane Cooling Scheme
46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2010An experimental approach is used to evaluate a baseline vane airfoil cooling configuration for advanced gas turbine engine application by incorporating arrays of two types of cooling holes at prescribed angles, spacing and sizes into large-scale flat plate specimens.
Jamie Johnson +7 more
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Overall Effectiveness of a Blade Endwall With Jet Impingement and Film Cooling
Journal of Engineering for Gas Turbines and Power, 2013Ever-increasing thermal loads on gas turbine components require improved cooling schemes to extend component life. Engine designers often rely on multiple thermal protection techniques, including internal cooling and external film cooling. A conjugate heat transfer model for the endwall of a seven-blade cascade was developed to examine the impact of ...
Amy Mensch, Karen A. Thole
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Journal of Turbomachinery
Abstract To keep metal temperature at allowable levels in modern gas turbine engines, both internal and external (film) cooling is necessary, which is represented by an overall cooling effectiveness. Previous studies measured overall cooling effectiveness for first stage vanes in low-speed experiments, where it is appropriate to use ...
Matthew Krull, Stephen Lynch
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Abstract To keep metal temperature at allowable levels in modern gas turbine engines, both internal and external (film) cooling is necessary, which is represented by an overall cooling effectiveness. Previous studies measured overall cooling effectiveness for first stage vanes in low-speed experiments, where it is appropriate to use ...
Matthew Krull, Stephen Lynch
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Volume 4: Heat Transfer, Parts A and B, 2012
The overall cooling effectiveness for a turbine airfoil was quantified based on the external surface temperature relative to the mainstream temperature and the inlet coolant temperature. This can be determined experimentally when the model is constructed so that the Biot number is similar to that of engine components. In this study, the overall cooling
Randall P. Williams +3 more
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The overall cooling effectiveness for a turbine airfoil was quantified based on the external surface temperature relative to the mainstream temperature and the inlet coolant temperature. This can be determined experimentally when the model is constructed so that the Biot number is similar to that of engine components. In this study, the overall cooling
Randall P. Williams +3 more
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Volume 5B: Heat Transfer, 2014
The laminated cooling or the layered cooling configuration with integrated impingement, rib-roughed and film cooling can result in a high overall cooling effectiveness and is believed to be a promising cooling technology for the next generation of advanced gas turbines. Previous studies found that the relative locations among the film hole, impingement
Xiao-Dong Zhang +2 more
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The laminated cooling or the layered cooling configuration with integrated impingement, rib-roughed and film cooling can result in a high overall cooling effectiveness and is believed to be a promising cooling technology for the next generation of advanced gas turbines. Previous studies found that the relative locations among the film hole, impingement
Xiao-Dong Zhang +2 more
openaire +1 more source
International Journal of Heat and Mass Transfer, 2016
Abstract The laminated cooling configuration with integrated impingement, rib-roughed and film cooling can result in high overall cooling effectiveness and is believed to be a promising cooling configuration for the next generation of advanced gas turbines.
Xiao-Dong Zhang +2 more
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Abstract The laminated cooling configuration with integrated impingement, rib-roughed and film cooling can result in high overall cooling effectiveness and is believed to be a promising cooling configuration for the next generation of advanced gas turbines.
Xiao-Dong Zhang +2 more
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Journal of Turbomachinery
Abstract Thermal design for the trailing edge of a turbine vane is critically challenging because the thinnest trailing-edge region has a low-thermal capacity, resulting in a much quicker thermal response to the hot gas. Cooling air for this region is usually extracted from the internal cooling passages inside the vane main body and thus
Xing Yang, Zihan Hao, Zhenping Feng
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Abstract Thermal design for the trailing edge of a turbine vane is critically challenging because the thinnest trailing-edge region has a low-thermal capacity, resulting in a much quicker thermal response to the hot gas. Cooling air for this region is usually extracted from the internal cooling passages inside the vane main body and thus
Xing Yang, Zihan Hao, Zhenping Feng
openaire +1 more source