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- W29787680 abstract "An experimental and numerical investigation on the flow separation in the corner between a wall and a vane in a highly loaded compressor cascade was performed. A large part of the total losses of a compressor stage is caused by this separation. The objective of the investigation is to understand the fluid mechanic mechanism of corner separation and to detect reference results for developing a flow control technique to avoid this flow separation. The experiments with a compressor cascade were carried out at a high-speed test facility at the DLR in Berlin. The experiments were done at Reynolds numbers up to Re = 0.6 x 10 (based on 40 mm chord) and Mach numbers up to Ma = 0.7. The profile of this blades represents the 10 % cut of vane length distance from the hub of the guide vanes of the single stage axial compressor of the Technical University of Darmstadt. For the assessment of the total pressure losses of the cascade (caused by the corner separation) a pressure measuring technique was used. To detect the separation area on the vane a flow visualisation technique was used. Different kind of flow control devices are intended to influence the corner separation. In order to optimize the devices for an application in turbomachines, an experimental study is currently ongoing, which investigates the use of such devices to reduce the losses of an aerodynamically highly loaded compressor cascade. In addition to the experiments, numerical computations were carried out with TRACE, a parallel Reynolds-Averaged Navier-Stokes flow solver, which has been developed for the simulation of turbomachinery flow. The computations were carried out with the same geometry as the experiments, including the measured inflow boundary layer conditions at the side walls." @default.
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- W29787680 date "2005-01-01" @default.
- W29787680 modified "2023-09-26" @default.
- W29787680 title "Experimental and Numerical Investigation of Secondary Flow on Compressor Blades" @default.
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