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Jian Liu, Mengyao Xu and Wenxiong Xi
To protect turbine endwall from heat damage of hot exhaust gas, film cooling is the most significant method. The complex vortex structures on the endwall, such as the development of horseshoe vortices and transverse flow, affects cooling coverage on the ...
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Lorenzo Cocchi, Alessio Picchi and Bruno Facchini
Experimental activity has been performed to study different impingement cooling schemes in static and rotating conditions. Geometry replicates a leading-edge cold bridge system, including a radial supply channel and five rows of film-cooling and showerhe...
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Ye Jee Kim, Gi Mun Kim, Youhwan Shin and Jae Su Kwak
The effects of dielectric barrier discharge (DBD) plasma on the film cooling effectiveness of a 30-degree slot was experimentally investigated in a low-speed wind tunnel. The pressure sensitive paint (PSP) technique was used to measure the film cooling e...
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Holger Werschnik, Marius Schneider, Janina Herrmann, Dimitri Ivanov, Heinz-Peter Schiffer and Christoph Lyko
The aerothermal interaction of the combustor exit flow on the first vane row has been examined at the Large Scale Turbine Rig (LSTR) at Technische Universität Darmstadt (Darmstadt, Germany). A baseline configuration of axial inflow and a variation of swi...
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Tsun Holt Wong, Peter T. Ireland and Kevin P. Self
The trailing edge of the high pressure turbine blade and vane presents significant challenges to the turbine cooling engineer. The current research has focused specifically on the effect of cutback surface protuberance, or ?land?, shapes on film cooling ...
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Rongguang Jia, Bengt Sundén, Petre Miron, and Bruno Léger
Pág. 635 - 645
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P. Martini and A. Schulz
Pág. 229 - 236
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J. E. Sargison, S. M. Guo, M. L. G. Oldfield, G. D. Lock, and A. J. Rawlinson
Pág. 453 - 460
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J. E. Sargison, S. M. Guo, M. L. G. Oldfield, G. D. Lock, and A. J. Rawlinson
Pág. 461 - 471
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