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48 5. RESULTS increases and flow separation occurs at the suction side of the blade. The vortex due to separation is much stronger than the tip vortex formed at the pressure side of the blade. The tip vortex formed at the leading edge detaches and is convected downstream between the blades. Downstream between the blades, the secondary flow at high mass flow contains three different structures; the detached tip vortex from the leading edge that is convected downstream, the tip vortex that is created between the blade tip and the shroud and a vortex that is counter-rotating as compared to the tip vortices, as depicted in Figure 5.11. Between the blades, the pressure gradient drives the flow in the boundary-layer at the shroud from the pressure side towards the suction side. When the flow in the boundary-layer at the shroud is affected by the strong jet that is formed at the tip, it is deflected inwards between the blades and a vortex starts to roll up. The higher mass flow at the inlet for Case 3 implies that the Mach number Figure 5.12. Snapshot of the velocity field in the diffuser, half a wheel diameter downstream of the trailing edge of the wheel, Case 1. The left figure shows the flow field with low mass flow through the turbine. The right figure shows the flow field when the mass flow through the turbine is high. is higher. When the mass flow through the wheel reaches its maximum, a shock wave is formed between the leading edge of the blade and the wall at the tongue. The shock disturbs the flow, and the tip vortex at the suction side at the leading edge where the shock occurs is very strong. Since the interval when supersonic flow occurs in the volute only corresponded to a few blade passages, it does not deteriorate the shaft torque. The higher mass flow for Case 3 also results in a stronger pressure gradient between the blades which gives a higher power output. Despite the stronger pressure gradient, the tip vortices for CasePDF Image | Numerical computations of the unsteady flow in a radial turbine
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