An audit of aerodynamic loss in a double entry turbine under full and partial admission

The current study investigates the sources of loss inside a mixed flow, double entry turbocharger turbine under steady inlet conditions in both full and partial admission. Under normal on-engine operation, it is likely that both limbs in adouble entry device will be fed by exhaust pulsations which are out of phase meaning that the turbine will spend most or all of the time with unbalanced flow through each limb. In the extreme case one limb will be flowing whilst the other is stagnant, this is the partial admission condition. Even under steady state inlet conditions, unequal admission is an important effect to study on the way to fully understanding pulsed operation of adouble entry device.

This paper presents 3D computational analyses of the flow inside adouble entry turbine under both full and partial admission. The computational results are compared to experimental results of Copeland (2009) and Copeland et al. (2010). The distribution of loss within the turbine is evaluated for each computational condition by means of entropy production. In the full admission case the most significant area of loss was found to be in the tip region. Under the partial admission condition the flow regime is very different. In this case the rotor wheel was found to be acting in a fully unsteady manner, with the flow being unable to reach a fully developed state throughout the flowing section of the volute. The most significant area of entropy generation in the partial admission case was associated with interaction of the flows in each sector of the volute, this occurred in the interspace between the nozzle exit and the rotor passage inlet.