A three-dimensional optimization procedure on the basis of a transitional Navier-Stokes code has been developed and tested. It allows complete three-dimensional parameterization of the flow channel for improved engine component design. Both the aerofoils and the end walls are three-dimensionally parameterized to permit full design control over the wetted surface. The end wall curvature is in fact controlled by the superposition of an axisymmetric and a nonaxisymmetric parameterization. The target comprises profile and secondary losses. The optimization procedure was applied to a low-loss turbine vane and resulted in an aerodynamic design with considerably reduced losses. Vanes and end walls were then manufactured according to this optimization. The high-speed cascade wind tunnel measurements performed on these parts confirm the computational results.

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