1. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 HS (a) and LS (b) turbine flow path Figure Legend:

2. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Scaling procedure validation for the T106C cascade [15]. (a) Pressure coefficient distribution (Re 2s = 1.6 × 10 5 ). (b) Kinetic energy loss coefficient as a function of streamwise distance Reynolds number. Figure Legend:

3. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Pressure coefficient distributions at HS and LS conditions: (a) 10% span, (b) 50% span, and (c) 90% span Figure Legend:

4. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Blade parameterization Figure Legend:

5. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 LS rotor redesign: pressure coefficient distributions at midspan and near endwalls for the optimum of OPT-02 campaign: (a) 10% span, (b) 50% span, and (c) 90% span Figure Legend:

6. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Redesign clouds Figure Legend:

7. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Pressure coefficient distributions at different sections along the span for the LS blade. Local shape refinements allow to match HS distributions near endwalls (OPT-03 campaign results). (a) 10% span, (b) 50% span, and (c) 90% span. Figure Legend:

8. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 LS blade geometry: (a) three-dimensional LS blade, (b) 30% span, (c) 50% span, and (d) 70% span Figure Legend:

9. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Kinetic energy loss coefficient for the HS and the LS blade as a function of the isentropic exit Reynolds number Figure Legend:

10. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Skin friction coefficient distribution for the HS and the LS blade for Re 2s = 0.15 × 10 −5 at rotor midspan Figure Legend:

11. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Spanwise distribution of the total pressure coefficient at stator inlet Figure Legend:

12. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Pressure coefficient distributions for the LS rotor blade: Re 2s = 0.8 × 10 5. (a) 25% span, (b) 50% span, and (c) 75% span. Figure Legend:

13. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Pitchwise mass-averaged radial distributions of the relative flow angle at the rotor inlet and outlet Figure Legend:

14. Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing J. Turbomach. 2016;138(11):111001-111001-9. doi:10.1115/1.4033259 Rotor pressure losses as a function of the exit Reynolds number Figure Legend: