TURBOdesign-2 has been applied to the design of a number transonic axial fans. An example is the design of a fore-ward swept fan rotor based on the well known NASA67 rotor.
Case Study : Forward Swept Transonic Fan Design
TURBOdesign-2 was recently used to re-design a conventionally swept fan based on the NASA67 rotor geometry. In this case study some of the results of this work are briefly discussed.
Fig. 1 : Characteristic of original NASA 67 rotor (blue), conventionally forward swept rotor (red) and forward swept rotor redesign by TURBOdesign-2. The main effect of forward sweep is to shift the characteristic to the left and hence reduce pressure rise at the original design flow rate. By using TURBOdesign-2 one can easily recover the pressure rise at the original design flow by changing the spanwise distribution of rVθ which is a design specification in Method 1.
(a) Conventionally forward swept rotor (b) Rotor designed by TURBOdesign-2
Fig. 2 : Comparison of the predicted surface Mach number near the suction surface. The results show the considerable reduction in shock strength in the rotor designed by TURBOdesign-2. This confirms the improvement in efficiency shown in Fig. 1.
Reference:
Watanabe, H and Zangeneh, M., 2003, "Design of the blade geometry of swept transonic fans by 3D inverse design." ASME paper No. GT-2003-38770
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