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- W2247489282 abstract "The main task in aerodynamic design of turbomachines is to create an annuhis and to define the turning of blades and vanes which in turn fulfils the performance requirements. The design process of multistage turbomachines is usually based on a quasi-three-dimensional model, which consists of coupled two-dimensional representations of the flow in the hub-to-tip and blade-to-blade plane respectively. The aerodynamic model used here is based on the calculation of the viscous flow along a streamplane of the meridian flow, which is representative for the pitch. The impact of three-dimensional effects and radial mixing on the circumferential averaged flow properties are taken into account with the aid of models for secondary flow and correlations for radial mixing. The process of averaging the governing equations in the pitch wise direction reduces the problem to two dimensions, thus requiring much less computational capacity and time than full three-dimensional models. Calculations have been carried out for an annular stator row with clearance at the hub and solidity of 1.0 at midspan. The comparison with the experiments, performed by Callus & Mertens,^ demonstrates that circumferential averaged Navier-Stokes methods with additional models for secondary flow and radial mixing can be a powerful tool in the design process of multistage axial compressors. It can give detailed information about the endwall boundary layers while requiring only a fraction of the computational time and space needed for full three-dimensional models." @default.
- W2247489282 created "2016-06-24" @default.
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- W2247489282 date "1999-04-14" @default.
- W2247489282 modified "2023-09-23" @default.
- W2247489282 title "Calculation Of Pitch Averaged Viscous Flow InAn Annular Compressor Cascade" @default.
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- W2247489282 doi "https://doi.org/10.2495/cmem990181" @default.
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