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Shroud suction surface Hub suction surface Shroud pressure surface Hub pressure surface Dimensionless length starting from inlet Figure 5.11.: The blade loading diagram of the rotor blade-to-blade analysis. The figure shows the mach number distribution of the hub and shroud suction and pressure surfaces respectively. 5.2. Detailed design The preliminary design presented above showed satisfactory off-design performance but the blade loading diagram indicated a poor impeller shroud contour. In the detailed design an attempt is made to improve the design of the shroud velocity levels. It can be seen in figure 5.11 that the fluid is quickly accelerated on the suction side and then decelerated toward the trailing edge. However the fluid is also accelerated on the suction side and just before the trailing edge the flow is overturned and the blade force is reversed. It would be preferable to attain a slow to moderate acceleration on the suction surface and just before the trailing edge decelerate to meet the flow on the pressure surface and thereby minimize the deviation. An attempt was made to accomplish this by changing the camberline blade angles and the thickness distribution. These changes are presented in figures 5.12 and 5.13. It would be possible to alter the end wall contour but after reviewing the b/rc distribution it was decided to leave it be. The flow on the hub side is not ideal but according to Aungier it is hardly possible to change this by adjusting the design. This is due to relatively low blade speeds and high blade angles. While this is true for the present case, the thickness is increased to protect the hub from centrifugal stresses and thereby ensuring the strength of the hub. The thickness of the hub contour at the trailing edge is decreased to insure a smoother transition at the exit. The hub camberline blade angles are changed to an inlet angle of 90 degrees (with respect to 62 Mach numberPDF Image | A Detailed Analysis of Radial Turbines
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