Abstract:

Flow in transonic axial turbines is very complex due to the existence of subsonic and supersonic regions, shock waves and non steady effects. In this conditions various phenomena, such as inlet blockage, cascade blockage and maximum load, and trailing edge vortex shedding appear.

The existing information about this subject both experimental and numerical is not systematic nor enough comprehensive. Consequently, we are developing a systematic numerical simulation work about this subject to prepare some educational documentation and numerical experiments in order that the students may learn and understand more easily this complex phenomenology. In that context the purpose of this contribution (virtual participation) is the submission of a paper complemented with a power point presentation, prepared to be used in theoretical classes, which contains the appropriate graphics, animations and explanations.

To achieve this goal we have selected a 2D test case, for which there is a detailed experimental information at various isentropic exit Mach number (M3is)= 0.85, 1.0, 1.11 and 1.43, to validate our computed results with ANSYS. After validation, we have extended the computational Mach range to have a complete description of the flow between M3is = 0.85 and the value of M3is at which the cascade is blocked, that is, the value at which there is no change in the computed flow as M3is is increased (M3is =2.1). Finally an analysis, discussion and preparation of the whole computed results is made for teaching purpose.

Keywords:

Transonic Turbines, Flow Simulation, Flow Animation.