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- W1964711898 abstract "This experimental work is to investigate film cooling for slot injection in separated flows. The purpose of this research is to study the feasibility of a highly loaded very thin turbine blade which has been devised in order to reduce weight and to save the coolant amount by simplifying the complicated internal cooling passages. With such a thin airfoil, a considerable flow separation is expected to occur on the pressure-side and film cooling practice in that kind of flow field has not been well established. In order to clarify the film cooling mechanism in the separated flows, experiments with a simple back-facing step flow with a single slot injection simulating the separated pressure-side flows were carried out. Very high lip thickness to slot height ratio up to 8 was considered. Adiabatic effectiveness as well as velocity and turbulence profiles downstream of the step was measured in detail. The experimental results showed that there is a clear improvement in the film effectiveness with the largest lip thickness case for whole range of the tested blowing ratio. The flow field measurements suggested that a large recirculation zone acted as buffer or resistance for flow mixing, which contributed to the improvement in the film effectiveness." @default.
- W1964711898 created "2016-06-24" @default.
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- W1964711898 date "2005-01-01" @default.
- W1964711898 modified "2023-10-05" @default.
- W1964711898 title "Film Cooling for Slot Injection in Separated Flows" @default.
- W1964711898 doi "https://doi.org/10.1115/gt2005-68119" @default.
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