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Radial Inflow Splitter Blades in Three-Dimensional

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Radial Inflow Splitter Blades in Three-Dimensional ( radial-inflow-splitter-blades-three-dimensional )

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low-speed radial inflow turbine. The flow was assumed to be incompressible and a finite difference scheme was used. He designed and constructed two different impellers, one of which was designed using the inverse approach described in Ref. 4. His work shows that the inverse designed impeller had a peak total-to-static efficiency 1.5 points better than the one designed using the conventional approach based on throughflow calculation technique. Ghaly (Ref. 3) extended the inverse design theory to compressible flow regime and used finite element method to numerically solve the equations. Zangeneh (Ref. 8) extended the work of Borges to compressible subsonic flow. He noted that the aerodynamically superior blade shape designed by the inverse approach showed 2.5% improvement compared to the impeller designed using the conventional approach based on throughflow procedure. More recently, Yang applied the inverse technique to a design study of radial inflow turbine wheel in three-dimensional flow (Ref. 1); the design specifications for the radial inflow turbine are summarized in Table I. It can be seen that this is a rather highly-loaded radial inflow turbine. Yang developed a rational technique for generating the swirl distribution (see chapter 4 for more details) from which the blading is then determined using the 3-D inverse design procedure developed in Ref. 4. His work has been focused on determining a blade geometry that will yield good aerodynamics without any due consideration to the structural aspect. In all his design calculations, he found that for a wide variety of swirl distributions there always exists a region of inviscid reversed flow on the pressure surface of the blade. Furthermore the resulting computed blade camber distribution is such that the blade filament is highly non-radial; this is particularly so in the trailing edge region. The fact that there exists an inviscid reversed flow region on the pressure surface implies the presence of strong adverse reduced static pressure gradient which may result in flow separation in real flows. Thus this aspect of his design calculations may be viewed to be inadequate in aerodynamic terms. The highly non-radial blade filaments in his design is also unsatisfactory from strutural

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