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does. This loss is estimated according to the model by Kacker and Okapuu (1981) and leads to slight over prediction compared to the CFD model. The finding is also in line with that of Persico et al. (2013), who found that the classical axial turbine profile loss models slightly overpredict losses in comparison with the numerical results in transonic turbine cascade. To make a general conclusion from the loss overprediction, more data should be available with different loss models and Mach numbers. 0.16 0.14 0.12 0.1 0.08 0.06 0.04 0.02 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 0.55 0.5 0.45 0.4 0.35 0.3 0.25 0.2 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 CFD CFD Benn seconda primary er et al. ry loss loss (2006b) seconda ry loss Benn Prim er et al. ary+Trai (2006a) ling edg primary e loss loss Benne r et al. ( 2006a) Aspect ratio [−] (a) Aspect ratio [−] (b) 0.5 0.4 0.3 0.2 0.1 0 0 0.02 0.04 0.06 0.08 0.1 0.12 0.5 0.4 0.3 0.2 0.1 0 60 65 70 75 80 85 Absolute flow angle [°] Total pressure loss coefficient, ω [−] h/c=0. h/c=0. h/c=0. h/c=1. h/c=1. 26 53 79 05 58 h/c=0.26 h/c=0.53 h/c=0.79 h/c=1.05 h/c=1.58 Persico et al. (2015) (c) (d) Figure 3: The effect of the aspect ratio on primary and secondary losses (a), the predicted penetration depth as a function of the aspect ratio (b), the effect of the aspect ratio on the spanwise total loss profile (c) and absolute flow angle (d). In the prediction of the passage vortex separation line, Eq. 4 predicts that the passage vortices should meet with the smallest studied aspect ratio at the trailing edge as shown in Fig. 3 (b). This means that the use of penetration depth correlation in Eq. 3 is justified also at the smallest aspect ratio in Fig. 3 (a), which makes the comparison between the cases also straight forward. In comparison, the numerical simulations predict that the secondary vortices merge before the trailing edge with AR=0.26, but also with AR=0.53 the vortices have merged. This merging behaviour is noticeable both in spanwise total pressure loss profiles in Fig. 3 (c) and in contour plots of Figs. 4 (a) and (b). In spanwise loss profiles the vortex merging also explains why the midspan losses in Fig. 3 (c) are clearly higher for the lowest two aspect ratios and also why the absolute flow angles for the same cases separate from others in Fig. 3 (d). When the AR is 0.79, two loss cores surrounded by separate vorticity peaks are visible in Figs. 4 (c) and (d), suggesting that two separate and relatively weak loss cores still exist. The influence of secondary flows on turning the flow angle is visible in Fig. 3 (d), which compares the current results with the ROT stator from Persico et al. (2015). The areas of over- 7 Blade span [−] Loss coefficient [−] Blade span [−] Z /h [−] tePDF Image | LOSS GENERATION IN RADIAL OUTFLOW STEAM TURBINE CASCADES
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