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16 3. TURBOCHARGERS, WITH FOCUS ON THE TURBINE 3.3. The rotor The rotor design is a compromise between aerodynamic performance, durabil- ity, weight and inertia and manufacturing cost. A rotor with low weight and inertia will respond fast to changes in load, but in order to reduce the weight, the rotor must be small, which leads to high velocities and sharp curvatures, which in turn decreases the aerodynamic efficiency. A design for good efficiency requires large blade passage areas to limit the gas velocity and small curvature of the blades to avoid separation and secondary flows. The specific work output of the turbine can be expressed with the Euler turbo-machine equation: WShaft =U1 ·Cθ1 −U2 ·Cθ2 (3.5) where Cθ is the tangential velocity component of the gas at the inlet and outlet, respectively. Uj is the blade speed, Uj = rj · ω. Station 1 is located at the rotor inlet and Station 2 at the rotor outlet, see Figure 3.5. For given rotational speed and radius, the maximum work output is achieved when the inflow tangential velocity component is high and the flow leaves the rotor in the axial direction. Figure 3.5. Rotor inlet (left) and outlet (right) velocity triangles. A conclusion from the Euler turbo-machinery equation (3.5) is that the optimum velocity at the inlet to the rotor is a pure tangential velocity, but it has been showed that this is not the optimum inlet angle. Moustapha et al. (2003) concluded that the optimum relative inlet flow angle is in the region -40◦ to -20◦ while Spence & Artt (1998) showed that a 99 mm radial turbine was reasonably tolerant to relative incidence angles between -40◦ to +30◦. An angle of incidence is positive when the inlet velocity tends to impinge on the blade tips at the pressure side of the blade. If the flow is more or less radial, itPDF Image | Numerical computations of the unsteady flow in a radial turbine
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