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18 3. TURBOCHARGERS, WITH FOCUS ON THE TURBINE turbochargers, which imply the manufacturers use the cut-and-try techniques (Flaxington & Swain (1999)), and therefore they have large databases for differ- ent designs. Doran et al. (2001) studied the effects of different shroud profiles at different operating points. In their experimental study, they used four different shroud profile radius for a 99.0 mm radial inflow nozzle turbine. The results showed that the largest shroud radius gave the best performance under most conditions, but at the highest rotational speed, the most shaped shroud profile gave 3.5 percent points better efficiency. They also performed one dimensio- nal numerical analysis to examine the effect of shroud profile with respect to incidence angle. For negative incidence angles, a small radius of shroud cur- vature gave the best performance, while for positive inlet angles, the largest radius gave the best performance. No measurements or 3-dimesional numerical computations were conducted in order to explain the effects of different shroud profiles. Another way to increase the efficiency of the turbine is to use back swept blades, which has for example been showed by Barr et al. (2006) by a numerical study for a turbine with an inlet tip diameter of 90 mm. They studied three different back sweep blade angles; 0◦, 15◦ and 30◦. At design condition, the efficiency was almost equally, while at off-design conditions, the efficiency was improved by 2% for the 30◦ back sweep angle blade due to a strongly reduced tip vortex at the leading edge. The drawback of this design is that it increases the bending stresses in the blade, and therefore limits the used of back swept blades. Palfreyman et al. (2002) studied the performance of four different turbine wheel geometries for a mixed flow turbine, and they concluded that a reduced chord length (with 18.75%) gave the largest deterioration of the efficiency, followed by a reduced number of blades (from 12 to 10), and then changing the inlet blade angle. The size of the gap between the blade tip and shroud also affects the efficiency, since the pressure gradient over the blade drives the flow over the tip and a jet and a tip vortex is created. Futral & Holeski (1970) performed an experimental study with the objective to study the effects of tip clearance for a radial turbine. The wheel diameter was 152.9 mm, which is quite large compared to the size of the wheel of an automotive turbocharger. Tip clearance values of 0.25 to 7% of the passage height at the rotor entrance and at the rotor exit were used. The results showed that an increase of the axial tip clearance at the rotor entrance gave a decrease of the total efficiency of 0.15% for each percent increase of tip clearance. At the exit of the rotor, an increase of the radial tip clearance from 1% to 3% of the passage height gave a decrease of the efficiency of 1.6% for each percent increase of tip clearance. For the range of 3% to 7% the decrease of efficiency was smaller, but still, larger than the effect of increasing the radial gap at the entrance. But, the tip clearance height is not the only parameter that affects the flow over thePDF Image | Numerical computations of the unsteady flow in a radial turbine
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