ABSTRACT
The radial-inflow turbines have been widely used in the turbocharger applications and the most common challenges for designing turbocharger turbines are to obtain good efficiencies for design point and off-design points, meeting the maximum mass flow requirement, having low moment of inertia and maintaining a good stress level which is quite difficult due to the very high tip speed and high turbine inlet temperature. The conventional way of tackling this multidisciplinary problem is to perform CFD/FEA analysis for a large number of designs (DOE) and build an RSM/surrogate model based on the design matrix then use optimiser to find the optimal solution. Inverse design method which is a 3D inviscid design method for turbomachinery blades has been used in the same way with some post modification/treatment on the blade geometry called radial-filament modification. In this paper, we proposed to use some aerodynamic and mechanical performance parameters from inverse design solution and a direct optimisation approach to perform the multidisciplinary optimisation. The final optimised design shows similar aerodynamic and mechanical performance as the baseline design (optimized through DOE) with significantly reduced number of CFD/FEA simulations.
