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a. Conventional Inducer The design was consistant with a normal high suction performance inducer. It was decided to have a three-bladed inlet to minimize the blockage and still obtain the required solidity in a reasonable axial length. The inlet geometry to the inducer was based on the theory of Ref 12. The tip blade angle was calculated to be 81.5 ° by this method. All other radial blade angles satisfy the condition for a right helix. The leading edge radii of the vane from hub to tip were constant over the trim. A nominal value of 0.010 in (0.00025 m) was used for the radius of the leading edge. Sharpness is not only an aid to cavitation performance but also affects the discharge head, as shown in Ref 15. Figures 13 and 14 show the blade element design performance prediction for the conventional inducer; these predictions are based on simple radial equilibrium. The loss coefficient and the deviation angles were taken from Ref 14, 16, 17, and 18. The validity of this type of analysis is shown in Figure 15, where the calculated and measured parameters are shown for the design of Ref 19. The only inputs necessary for this analysis are the streamline blade deviation angles and loss coefficients. The discharge flow coefficient of the forward inducer section was increased to obtain a value midway between the inlet and transition discharge. In order to maintain the constantly increasing head, the blade angles were decreased along the mean streamline by the relationship = 1 - _ . The blade thickness at the root was designed for minimum cotan B blockage, consistant with stress requirements. Stress levels were computed from 'worst case' conditions accounting for both fluid and centrifugal loading. b. Hubless Inducer In order to determine some design criteria for the inlet geometry of the hubless inducer, a computer program was developed which had four options for the type of flow which existed radially across the inducer inlet. The analysis obtained from this model, while qualitative, gave some insight to the flow conditions. The four flow options in the inducer inlet were free vortex, forced vortex, power vortex, and zero angular fluid velocity. The flow within the inducer blade passage was assumed to follow the blade after the blade had reached a solidity of 1.0 along any given streamline. In all cases, it was also assumed that the total head within the inducer eye was equal to that of the free stream inlet pressure. With these assumptions it was found that only the fourth type of flow field, zero angular velocity, could exist at the inducer inlet and support simple radial equilibrium. Secondly, it also became apparent that the smaller the inlet angle was the larger the inlet blade tip angle must be. This is caused by the limit in the rate of head increase, in the axial direction, generated by the blade above the free fluid. Large head increases along the tip streamline caused the flow to shift to the tip and the axial velocity of the free fluid to go to zero. Large inlet angles permit faster head increases along the streamlines within the blade. 21PDF Image | HUBLESS INDUCER FLOW HYDRAULIC TURBINE INDUCER BOOST PUMP
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