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Figures 17 and 18 show the predicted performance of the transition section at the design flow. The inlet flow coefficient and mean radius was obtained by assuming constant angular momentum at each streamline discharging from the forward section. The discharge flow coefficient and mean radius had previously been selected during the one-dimensional analysis (Section Ill,C). B. ROTOR The detailed design of the rotor was initiated after the inducer testing had been completed. Therefore, some adjustments were made to the design specification of the rotor based on the test data. The only parameter in which there was a significant variation was the required torque to drive the inducer-shroud combination. Torque was measured at 30% greater than that estimated during the parametric analysis (Section III). This discrepancy will be discussed in later sections, but its only effect on the rotor was to require a higher head rise due to additional turbine head drop necessary to produce the required torque. The required head coefficient increased from 0.16 to 0.195 at the mean; this was still within the design limitations given in Ref 5. Since the inducer average head and head distribution from test predicted, the rotor inlet absolute fluid flow was assumed to be The predicted blade element performance of the rotor is shown in Figures 20 and 21. The blade inlet angles were set to give positive incidence at all radial sections for improved cavitation performance, and were greater than minimum loss incidence. The blade turning was then adjusted to obtain the required average head rise with nearly uniform discharge axial velocity. The maximum diffusion factor of 0.525 occurs at the tip stream line. C. TURBINE Both the turbine and rotor were designed after the inducers were tested; therefore, the power required to drive the inducer-shroud was known through direct measurement. Two types of turbine blading were considered, constant section and twisted section. Since the relative inlet flow angle and a very wide variation hub to tip and because a wide operating range was desired, a constant section blunt leading edge blade was selected. This type blade, data was as the same as Figure 19. the inducer were followed for the rotor. The mass average head rise of the rotor was determined from the overall required system head rise, the inducer head rise, and the head drop through the turbine, There were several design iterations between the rotor and turbine to determine the best combined system, based on the design specification and blade geometry. the predicted inducer discharge, adjusted for the speed difference, The same design methods used to design the transition section of 27PDF Image | HUBLESS INDUCER FLOW HYDRAULIC TURBINE INDUCER BOOST PUMP
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