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From the existing information, the current study continues the already ongoing evaluation of the suitability of axial turbine loss correlations on the radial outflow turbine performance prediction by evaluating the accuracy of relatively recent methods. Special attention is also paid to the loss source analysis of ultra-low AR blades. First, the modelling methods are described, and second, they are followed by a presentation of the examined blade geometry. Third, the results of the grid dependency study are presented. Finally, the effects of the AR and incidence are studied and compared with axial turbine loss correlations. METHODS Numerical methods The Navier-Stokes solver Finflo is used in this study. The solver has been succesfully used to model both linear (Gro ̈nman et al. 2013) and centrifugal turbine cascades (Harinck et al. 2010). It employs the finite-volume method for spatial discretisation and uses a constant specific heat capacity at constant pressure. More detailed information about Finflo and different numerical methods can be found e.g. in a paper by Siikonen (1995). In this study, a k-ω-SST turbulence model (Menter 1993) without wall functions has been used, and the fluid is modelled as an ideal gas with R=462.5 J/kgK and γ=1.32. This assumption is reasonable since the compressibility factor of dry steam at relatively low operational pressure and temperature levels is close to unity during the whole expansion. Uniform momentum and total enthalpy distributions are defined as the inlet boundary condi- tions, and a constant static pressure distribution is used as the boundary condition at the outlet. Where applicable, cyclic boundaries are employed. The boundary conditions are presented in Fig. 1 (a). Additionally, the hub and shroud walls are modelled as solid walls in three- dimensional models, and in two-dimensional models, symmetry boundary condition is used. In post-processing the values at the inlet are calculated slightly downstream from the inlet bound- ary (plane 1), and at the outlet, slightly upstream from the outlet boundary at 48% of the radial chord (plane 2) downstream from the trailing edge to ensure fully mixed out conditions. The values at the circumferential measurement planes 1 and 2 are mass flow averaged. (a) (b) Figure 1: Example of the modelled geometry with h/c=0.26 (a) and the real turbine rotor geometry after test milling (b). During the simulations, the convergence is monitored by following the mass flow difference 3PDF Image | LOSS GENERATION IN RADIAL OUTFLOW STEAM TURBINE CASCADES
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