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Radial turbine preliminary design and performance prediction

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Radial turbine preliminary design and performance prediction ( radial-turbine-preliminary-design-and-performance-prediction )

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Δp0 Relative Pressure Loss α Flow Angle β1_opt Inlet Optimum Blade Angle Subscripts 4 Rotor inlet 5 Rotor outlet m meridional t throat INTRODUCTION Radial turbines find nowadays-widespread use in turbochargers for automotive applications and for auxiliary power units. The main features are compact design, a higher efficiency at high numbers of revolutions, low expansion ratios and high power-to-weight ratio. The main elements for radial turbine are in the order: the inlet volute, the stator nozzle, the rotor and, finally, the exhaust diffuser, as shown in Figure 1. 1 = volute inlet parameter 2 = volute exit and nozzle inlet parameter 3 = nozzle exit parameter 4 = rotor inlet parameter 5 = rotor exit parameter 6 = diffuser exit parameter FIGURE 1. Radial Turbine Stage Cross Section In this work will be analyzed the rotor design, that it is the element that most influence the performance of the entire turbine. Indeed, it is the turbine’s component where the major energy losses occur due to friction between the flow and the blades, and the transition from laminar to turbulent flow conditions. The geometry of the blade channel affects the elaborated mass flow. The motion of the flow from the end towards the inside of the blade at the hub radius determines power generation, and then work exchange. It also decreases the speed of tangential component that generates a high-pressure gradient along the vane channel. At the output of the rotor, the flow is axial, the radial velocity component is zero, and the flow angle is equal to 90°. For radial inflow turbines, the inlet section of the rotor blades is generally radial. The parameters that influence the rotor geometry are represented by the loading coefficient and the flow coefficient [1]: 020097-2

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