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J/ ,1_FndwallFlow Passage Flow Stator Endwall Figure 4: Predicted flow visualisation for the stator endwall and suction surface using the Dawes code Rotor Blade numbers. Stressing considerations dictate that the camberline of the rotor blades are formed from radial elements. Near to the leading edge, the rotor blades are radial. A simple analysis shows that for incompressible flow between radial blades of a many- bladed impeller, the velocity jump across the blades EW is given by AW 4tt UZ (5) so that the loading is simply determined by the number of blades. Slip factors and therefore optimum inlet loading are also thought to be independent of Mach number below 0.8 (see Stanitz (1952)), further suggesting that the number of blades in the rotor of the model should be the same as in the full size machine. The effects of blade lean at rotor inlet . In the high-speed turbine, the rotor leading edge is leaned so that the pressure side is towards the shroud. Because the density of the flow in the model turbine is effectively constant, the width of the inducer had been increased by a factor of about 2. This presented a difficulty as to the choice of the scaling parameters which should be used to specify the angle of lean in the low-speed rotor. A need for a simple analysis therefore existed. The analysis described in appendix A is applicable to the general case where shroud curvature exists at the leading edge plane but where there is no blade curvature. Figure Al shows a plan and meridional view of the rotor blades in the region of the leading edge together with the leading dimensions of the problem. The result of the analysis shows that the important modeling relationship is: Figure 6: Mid passage blade-blade relative Mach number contours Velocity vectors, in the meridional view, show the movements of the secondary flows for the different sections of the turbine (see figure 7). Comparison between the two turbines is good. As with the predictions of Zangeneh et al (1988), the secondary flow moves towards the hub on the pressure surface exducer and towards the shroud on the suction surface exducer under the influence of the reduced static pressure gradient. The effects of tip clearance flows may also be observed on both surfaces and in particular movement of low momentum flow up the exducer pressure surface towards the clearance region is apparent. The comparison between the full size turbine and the model is thought to be adequate to provide a representative turbine on which to undertake aerodynamic research. TEST FACILITY The rig operates as an open loop wind tunnel drawing air from the atmosphere into the model turbine. The turbine exhausts into a circular duct which connects to a sliding throttle and the centrifugal fan. The open loop configuration with the suction fan after the working section ensures that axisymmetric, low turbulence flow can be obtained at entry to the blade row under investigation. The stator blades were made from a glass reinforced epoxy resin cast from a machined mould. Each stator blade is mounted on two pins so that the stagger angle is correctly fixed. The measured variation of throat area corresponds to a variation of less than 0.2° in stator exit angle and 4° in rotor incidence. The rotor blades were manufactured by a slightly different process. A mould was again produced then a gel-coat of epoxy resin was placed in the mould and allowed to harden before a resin foam was injected into the mould. In this way light, rigid blades were obtained. Static pressure tappings were cast into both the stator and rotor blade surfaces. V(Vhu t) Vshroud) _b U- — ( - ` m2 r2 tanO A7) where all terms are defined in Appendix A. The analysis is for the general case where there is meridional curvature. However, for the present study, the rotors under consideration have no meridional curvature at the leading edge and using the method described by Casey and Roth (1984) for analysing sweep the effective blade curvature is 1.6°. The blade lean has been applied solely to reduce the loading. The blade force is therefore unopposed by streamline curvature forces and the flow is deflected towards the hub. For similarity of flow conditions between the full- size and the model it follows that the value of b/ rtanO should be preserved. Applying the above equation to the adopted blade geometry for the model results in a 5% variation of absolute velocity across the span, corresponding to an incidence variation of +9 °. Such a large variation in incidence onto a radial leading edge geometry is expected to increase losses but will be representative of existing radial inflow turbines and interesting to analyse. Flow direction -- L.E. I ill T.E. Suction Surface Analysis of the rotor design using viscous flow predictions . For comparison between the predicted flowfields for the two machines, mid passage meridional and blade-blade relative Mach number contours are presented in figures 5 and 6. Although the two turbines are not identical the comparison appears to be reasonable. Full size Figure 5: Meridional mid passage relative Mach number contours Downloaded from http://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT1991/78989/V001T01A077/2400491/v001t01a077-91-gt-220.pdf by guest on 23 January 2021PDF Image | Design and Testing of a Radial Flow Turbine for Aerodynamic Research
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