LOSS GENERATION IN RADIAL OUTFLOW STEAM TURBINE CASCADES

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LOSS GENERATION IN RADIAL OUTFLOW STEAM TURBINE CASCADES ( loss-generation-in-radial-outflow-steam-turbine-cascades )

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blade due to separate hub and shroud secondary structures, but especially the last 40 per cent of the blade surface on the suction side is clearly affected, although the influence of incidence is practically negligible. These changes in loading are further connected to the merging of secondary structures at the midspan. 0.8 0.6 0.4 0.2 0 0 0.2 0.4 0.6 0.8 1 Blade surface coordinate [−] (a) (b) (c) Figure 5: The effect of incidence on primary and secondary losses (a) and the isentropic Mach number distribution on 2D (b) and 3D geometries (c). 0.15 0.1 0.05 0 −10 −5 0 5 10 Incidence [°] 0.8 0.6 0.4 0.2 0 0 0.2 0.4 0.6 0.8 1 Blade surface coordinate [−] Primary loss Secondary loss Primary loss Benner et al. (1997) i=0 i=10 i=−10 i=0 i=10 i=−10 0.5 0.4 0.3 0.2 0.1 0 0 0.02 0.04 0.06 0.08 0.1 0.12 Total pressure loss coefficient, ω [−] 0.5 0.4 0.3 0.2 0.1 0 70 72 74 76 78 80 Absolute flow angle [°] Design i=−10° i=10° h/c=0.26 Design h/c=0.26 i=−10° i=10° (a) (b) (c) (d) Figure 6: The effect of incidence on the spanwise total pressure loss coefficient (a), absolute flow angle (b), and contours of vorticity at negative (c) and positive incidence (d) in plane 2. The influence of positive incidence on spanwise total pressure loss is reasonably high above 10% of the span in Fig. 6 (a). There is a noticeable change in the position and strength of the vorticity (and total pressure loss) in the mentioned area, as shown in Figs. 6 (c) and (d), and it was linked to increasing secondary losses. However, only a minor effect is seen in Fig. 6 9 Blade span [−] Blade span [−] Loss coefficient [−] Isentropic Mach number [−] Isentropic Mach number [−]

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