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.
Experimentally Verified Numerical Optimization of a Three-Dimensional Parametrized Turbine Vane With Nonaxisymmetric End Walls
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Atlanta, GA, June 16–19, 2003. Manuscript received by the IGTI December 2002; final revision March 2003. Paper No. 2003-GT-38624. Review Chair: H. R. Simmons.
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Nagel , M. G., and Baier, R. (May 5, 2005). "Experimentally Verified Numerical Optimization of a Three-Dimensional Parametrized Turbine Vane With Nonaxisymmetric End Walls ." ASME. J. Turbomach. April 2005; 127(2): 380–387. https://doi.org/10.1115/1.1773848
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