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- W2312883952 abstract "Computational investigations were carried out on a highly loaded linear gas turbine cascade, where one end-wall was cooled by a single row of simple film cooling holes of diameter ‘d’, whose axes made an angle of 30 with the end-wall. The computations were carried out using the tool Ansys Fluent 15.0, with the film hole row at 5 different stream-wise locations 8d, -4d, 0, +4d and +8d from the leading edge, for a fixed blowing ratio of 0.6. Air was considered as the mainstream hot fluid and carbon-di-oxide (CO2) gas was the film coolant injected through the holes. The film hole pitch was maintained at 2d for all the stream-wise locations. The mainstream flow Reynolds number (Re) based on the air properties at the cascade inlet and blade actual chord length being greater than 2E+5, indicated that the flow was turbulent at the inlet. Stream-wise variation of pitch-wise averaged adiabatic film cooling effectiveness on the cooled end-wall has been discussed. Distribution contours and local variation of adiabatic effectiveness in the pitch-wise direction have also been presented at chosen locations. . For the location immediate downstream of the film hole row ie., at x/d = 6, highest values of η was observed, with the peak value reaching up to 0.87. Highest spread of the �� was found on the end-wall for the film hole row located at x/d = 0. The structures of the flow development downstream of the film holes are presented to understand the fluid dynamics in the system." @default.
- W2312883952 created "2016-06-24" @default.
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- W2312883952 date "2015-07-23" @default.
- W2312883952 modified "2023-09-25" @default.
- W2312883952 title "Computational studies on End-wall Film Cooling from a Single Row of Holes at Different Stream-wise Locations in a Gas Turbine Cascade" @default.
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- W2312883952 doi "https://doi.org/10.2514/6.2015-3731" @default.
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