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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Figure 4.1.: The geometry of the modeled rotor is specified on the hub and shroud contours. A series of points connecting the two contours are defined using radial and axial coordinates. 4.1. The first radial turbine The tests by Volvo Powertrain AB were performed in a so called ”cold-rig”. The turbine is designed to run at a high inlet total temperature, however, when Volvo run their tests the inlet total temperature was held at 373K. Additionally the turbine was scaled by a factor of 0.7. In light of this, two different analyses were performed. One where the turbine was scaled and operating at flow conditions similar to those at which the tests were made and one where the turbine was not scaled and the flow conditions were similar to those at which the turbine was designed to operate at. This was done to evaluate if it made any difference to the results. The test results was provided by Volvo Powertrain AB. Only the expansion ratios were given and, consequently, it was necessary to calculate the inlet pressures from these ratios. The speed and mass flow are given as corrected mass flow and corrected speed respectively. They were converted to give the appropriate mass flow and speed using equation (3.5). 4.1.1. Simulations on the original turbine The first simulation used the original geometry and inlet conditions. An attempt was made to resemble the actual gas which is supposed to flow through the turbine, the mole fractions of this gas are shown in table 4.1. The geometry was given as coordinates and imported to program ”RIGPAC” in ”TurbAero”. From ”RIGPAC” the mean-line geometry was exported to ”RIFT”. No diffusor was used and a volute was created, using ”VOLDES” in ”TurbAero”, to guide the flow onto the nozzle blades with as little 41

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