Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Schematic coaxial cascade section; left: turbine blade element (BE) with control volume (CV), velocity triangles, and induced angular force δFu; right: vector mean relative flow velocity and flow angle

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Skewed Wells turbine rotors; left: backward skewed blade (δ < 0 deg); middle: straight blade (δ = 0 deg); right: forward skewed blade (δ > 0 deg); all forms can be combined in one blade

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Wells turbine rotor; left: loss analysis; right: blade element (BE)

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Local lift correction μloss as a function of the distance from a wall at y/L = 0 for various constant skew angles δ

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Numerical domain

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Test facility: (a) housing, (b) splitter attenuator, (c) centrifugal fan, (d) splitter attenuator, (e) plenum, (f) honeycombs and turbulence control screens, (g) nozzle, (h) static pressure measurement, (i) static pressure measurement, (j) honeycombs, (k) turbine section; dimensions in mm

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Acoustic measurement setup (j) honeycomb screen, (l) nose cone, (m) rotor with torque flange, (n) flow traverse position, (o) generator, (p) generator struts, (q) reference sound source (RSS), (r) microphone; dimensions in mm

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Comparison of turbine (Lp) and background sound pressure (Lp,bgn) at microphone position according to Fig. 6; turbine is operated at its design point; frequency resolution: Δf = 8 Hz

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Complete set of aeroacoustic steady-state characteristics; (a) flow coefficient, (b) power coefficient, (c) total-static efficiency, (d) specific sound power level

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Measured and predicted flow field data: radial distributions of circumferentially averaged rotor exit flow quantities (traverse position (n), Fig. 7) at ψts = 0.38; (a) axial velocity, (b) circumferential velocity, (c) blade work

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Blade loading at the hub from RANS (ψts = 0.38, r/rtip = 0.51)

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Blade area with separated flow versus turbine pressure head (from RANS)

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Skin friction coefficient and “surface” stream lines at suction surface; ψts = 0.38 (from RANS)

Date of download: 10/15/2017 Copyright © ASME. All rights reserved. From: Effect of Blade Skew Strategies on the Operating Range and Aeroacoustic Performance of the Wells Turbine J. Turbomach. 2013;136(1):011003-011003-11. doi:10.1115/1.4025156 Figure Legend: Measured narrow band sound power spectra; (a) ψts = 0.38, (b) ψts = 0.60; frequency resolution of Δf = 8 Hz