Mean-Line Design of a Supercritical CO2 Micro Axial Turbine

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Mean-Line Design of a Supercritical CO2 Micro Axial Turbine ( mean-line-design-supercritical-co2-micro-axial-turbine )

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Appl. Sci. 2020, 10, 5069 12 of 20 (a) (b) (c) Figure 7. Flow coefficient (φ) versus (a) flow angles [β2 and α2] (b) Mach number at the rotor inlet [Ma2] and exit [Ma3] (c) normalised efficiency [ηtt] and swirl angle [α3] (d) blade heights [b2 and b3] at various rotational speeds. Furthermore, increasing the flow coefficient results in an efficiency decrease at all rotational speeds, as observed in Figure 7c. Additionally, it results in a decrease in swirl angle from 26 to 5◦. However, at high flow coefficients, low swirl angles and low rotor inlet blade angles (α2) are achieved. Increasing the flow coefficient results in higher Mach number at the rotor exit and hence higher losses incurred by the formation of shock waves in the rotor blade passages. Additionally, profile losses will be higher owing to the boundary layer growth, whilst friction losses at the exit are expected to be high. Consequently, a drop-in efficiency is observed at higher flow coefficients. The effect of changing the flow coefficient on the blade heights is shown in Figure 7d. Increasing the flow coefficient resulted in a decrease in both blade heights at all speeds. A minimum inlet blade height of 0.24 mm is found at a rotational speed of 150 kRPM and flow coefficient of 1.0. The effect of changing the aspect ratio on the turbine efficiency is shown in Figure 8a. Increasing the aspect ratio from 1 to 3 resulted in the normalised efficiency increasing from 0.987 to 1.000 at 250 kRPM. Higher aspect ratios result in lower rotor and stator losses and higher efficiency. For high aspect ratios, secondary effects are confined to the end-wall region. However,it affects the whole passage for small aspect ratios [44]. The gas bending and centrifugal tensile stresses have been (d)

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