Simulation of a 3D unsteady flow in an axial turbine stage
Aeronautical Research and Test Institute, Plc, Beranovýh 130, 199 05 Praha–Letnany
The contribution deals with a numerical simulation of an unsteady ﬂow in an axial turbine stage. The solution is performed using an in-house numerical code developed in the Aeronautical and Test Institute, Plc. in Prague. The numerical code is based on a ﬁnite volume discretization of governing equations (Favre averaged Navier-Stokes equations) and a two-equations turbulence model. The temporal integration is based on the implicit second-order backward Euler formula, which is realized through the iteration process in dual time. The proposed numerical method is used for solution of the 3D, unsteady, viscous turbulent ﬂow of a perfect gas in the axial turbine stage. The ﬂow path consists of an input nozzle, stator blade-wheel, rotor blade-wheel, a shroud-seal gap and a diffuser. Attention is paid to the inﬂuence of a secondary ﬂow structures, such as generated vortices and ﬂow in shroud-seal gap.
© Owned by the authors, published by EDP Sciences, 2012