Abstract
To improve the prediction of compressible flow in highly loaded turbomachinery components a modified high resolution scheme to solve the Navier Stokes equations has been developed. The scheme is based on the methods introduced by Osher and Roe. For high efficiency, an implicit iterative solution procedure is used. The code is validated, presenting highly accurate computational results. A structured grid is used during the investigations and a special grid topology for turbine vanes is presented. As the guide vanes are designed using CAD software the CFD code is coupled via the standard interface IGES (Smith et al., 1988). Starting with classical design principles, a first guide vane is designed. Based on flow field computations, the design of the guide vanes is improved successively. Resulting from the experiences gained during the improvement procedure general design principles are formulated.
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