Optimised Radial Turbine Design D1.8

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Optimised Radial Turbine Design D1.8 ( optimised-radial-turbine-design-d18 )

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Starting with the blade loading coefficient, as shown in figure 6 the maximum efficiency of the loading coefficient ranges between (0.8 - 0.1). In the designed program starting with a value of 0.8 an iterative process is followed until reaching a value where the incidence loss would is minimised. Another important parameter is the exit flow coefficient which is related to the loading coefficient as shown in figure 6. It is clear that the best efficiency range is (0.2- 0.3), a value of 0.25 was chosen as it corresponds to the highest efficiency. The ratio of axial length to rotor inlet radius( )was chosen to be 0.7 as recommended by Whitefield and Baines 1990 as this geometric value depends on past experience and there are no correlations to determine it. The value of exit hub to inlet tip radius ratio( )was chosen to be 0.3 according to Baines 2003 and Jacob et al 2012. The rotor meridional velocity ratio normally has a value near 1.0 as suggested by Baines 2003. Figure 6: Correlation of attainable radial turbine efficiency Baines (2003). A stator loss coefficient of 0.08 was assumed, which is feasible for the turbine stator. The turbine total to static efficiency assumed to be 90%; this means that this design is aiming for higher efficiency than the target. For designing the nozzle guide vanes design, the vane chord to rotor inlet diameter ( ) was selected to be 0.3 as suggested by Heitt and Johnston 1964. The values of Vane chord to vane pitch (solidity) ( ), Thickness of vane leading edge to vane chord ( ) and thickness of vane trailing edge to vane height ( ) where given values of 1.2, 0.285 and 0.12 respectively following the recommendations of Aungier 2006. The interspace geometry value ( ) recommended by Watanabe et al (1971) for minimum losses was suggested to be two. 8

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