Abstract
Numerical simulations of 2D compressible flow through the tip-section turbine blade cascade with a flat profile and the supersonic inlet were carried out by the OpenFOAM code using the Favre-averaged Navier-Stokes equations completed by the γ-Re_θt bypass transition model with the SST turbulence model. Predictions completed for nominal regimes were concentrated particularly on the effect of the shock-wave/boundary layer interaction on the transition to turbulence. Further, the link between the inlet Mach number and the inlet flow angle i.e. the so called unique incidence rule was studied. Obtained numerical results were compared with experimental data covering optical and pressure measurements.
Highlights
The compressible flow through the tip-section of turbine blade cascade of the low-pressure part of steam turbine of large output is influenced by high circumferential velocities
The blade cascade TR-U-8 was designed for two nominal regimes given by the inlet Mach number M1 = 1.2 and isentropic outlet Mach numbers M2is = 1.7 and 1.9
Numerical simulations of 2D compressible flow through the tip-section turbine blade cascade with the supersonic inlet were accomplished for various boundary conditions
Summary
The compressible flow through the tip-section of turbine blade cascade of the low-pressure part of steam turbine of large output is influenced by high circumferential velocities. A direct link between the inlet Mach number and the inlet angle exits According this so-called unique incidence rule (see Lakshminarayana [3]) the inlet flow angle is prescribed at the domain inlet and actual inflow parameters are determined in the distance about one chord upstream of the leading edge plane. The flow structure is affected mainly by the interaction of the exit shock wave with the shear layer on the suction side of the adjacent blade and by the interaction of the inlet shock wave upstream the blade leading edge with the shear layer on the pressure side of preceding blade, see Luxa et al [8]. Numerical simulations of the 2D compressible flow in a turbine blade cascade with the supersonic inlet were realized for the cascade TR-U-8 representing the tip-section of the rotor blade with a flat profile. Musil et al / Applied and Computational Mechanics 15 (2021) 1–10 aim of predictions carried out for nominal conditions was focused on the effect of the shockwave/boundary layer interaction on the laminar/turbulent transition at various inlet free-stream turbulence intensities
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