A Detailed Analysis of Radial Turbines

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A Detailed Analysis of Radial Turbines ( a-detailed-analysis-radial-turbines )

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When c6m > a6 a shock wave might occur adding losses. To include these losses they have to be modeled. It is possible to use variable nozzle blades, which often is called a ”VGT”-arrangement. In this arrangement the nozzle blades can be turned to hold up a constant pressure level at the inlet to the nozzle blades. The fact that the blades are turned inevitable means that a clearance at the tip and bottom will arise. Baines shows that this clearance becomes significant when the blade width becomes small and that the loss which arises from it must be taken into account [12]. The losses arise due to the fact that the leakage flow is not turned to the same degrees as the flow inside the nozzle row which can cause large incidence at the impeller tip. Qiu et. al. developed a mean-line method to predict the losses which arise from the clearance [16]. Their conclusion is the same as Baines’s with the addition that with a smaller nozzle opening, the clearance effect decreases and that the presence of a clearance increases the choking limit of the nozzle. The Impeller The performance analysis of the impeller is far more difficult and complex than those of the other components. The fluid is in general turned 90 degrees and this generates hub- to-shroud flow profile gradients which are difficult to model. The geometry is specified at the inlet, the mid passage, the outlet and the throat. The geometry variables are presented in table 3.4. The geometry can be seen in figure 3.10 and in figure 3.11. r9s r9h Figure 3.10.: The geometry of the impeller vanes. There is a greater amount of different losses which have to be taken into consideration besides the ones described for the volute and the nozzle row. Aungier defines six loss 32 r7

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