1. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 3D CFD–TzFlow comparison (a) total pressure field (P 0 ); (b) entropy field (s); (c) spanwise profiles of relative flow angle (β) at stage inlet and rotor exit; (d) spanwise profiles of absolute flow angle (α) at rotor exit and stage exit Figure Legend:

2. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Layout of the optimization procedure Figure Legend:

3. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Axial compressor stage geometry—baseline configuration Figure Legend:

4. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Example of 3D blade geometries constructed by the use of 2D multiple profiles Figure Legend:

5. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Convergence history of the optimization. (a) Comparison between Kriging and FFNN metamodels. (b) Comparison between the computed and predicted (meta-) values by Kriging metamodel for objective function φ and constraint χm·. Figure Legend:

6. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Flow surface in bladed regions for the baseline and optimized configurations Figure Legend:

7. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Total enthalpy distribution in the baseline and optimized configurations Figure Legend:

8. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Entropy distribution in the baseline and optimized configurations Figure Legend:

9. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Spanwise distributions of relative (a) and absolute (b) flow angles, tangential velocity (c), and total enthalpy (d) for the baseline and optimized configurations Figure Legend:

10. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Blade profile comparison between optimized and baseline configurations Figure Legend:

11. Date of download: 7/8/2016 Copyright © ASME. All rights reserved. From: Optimization of Turbomachinery Flow Surfaces Applying a CFD-Based Throughflow Method J. Turbomach. 2013;136(3):031013-031013-11. doi:10.1115/1.4024694 Spanwise profiles of β at stage inlet and rotor exit (a), α at rotor exit and stage exit (b), total enthalpy rise (c), and total pressure rise (d) for the baseline and optimized configurations as computed with the high-fidelity CFD model Figure Legend: