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2 .3 .4 .5 .6 .7 .8 Specific speed, N s, dimensionless o I ' 2.S Iii jti la! Design ct)r. a> ^ •u .70 Yo Fig. 14 Rotor configurations investigated (7) ume flow and mass flow, or some combination of these could be employed. The flow area approach has advantages in system size and system duct and heat-exchanger pressure drops. The 12.6-cm turbine mentioned previously (6) was modified to accept a series of stator blade rows with different numbers of `,lades and 6 " ivy Specific speed, N s,(rpmHft 3/4i/secI 12 (bi Static efficiency. Fig. 15 Variation of efficiency with specific speed at equivalent design speed with best stator-rotor combination_) ! 7i t,lade arI les. The rotor was fitted with an ex- tension for reduced area operation and was also cut back for increased area operation. These modifications were employed to vary stator throat area from 20 to 144 percent of the design throat area and rotor throat area from 53 to 137 percent. Fig. 11+ shows the rotor as designed, with the reducing extension, and cut back. Details on the geometry, test results, and internal velocitr calculations are described in reference (7). Performance was then experimentally deter- mined for 13 combinations of stator area and rotor area. Fig. 15 shows the envelopes of the design-speed efficiency curves obtained with each rotor configuration. Specific speed for each stator-rotor combination was varied simply by varying overall pressure ratio at design speed. Note that total efficiencies over 0.90 were measured for specific speeds between 0.t7 and 0.80. At the high and low ends of the hi;i efficiency range of specific speed, the ratio of stator throat area to rotor throat area was near the design ratio. Efficiency was lower for area ratios not near the design ratio. The best combinat.1 on 1 n terms of design area were 112 to C 10-3533 1. GO .90 7- 80 i o .70 E/rTh\ / Configuration —With design rotor ---With rotor extension ------With cutback rotor c/ \ 20 30 40 50 60 70 80 90 100 110 Downloaded from http://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT1972/79818/V001T01A041/2390888/v001t01a041-72-gt-42.pdf by guest on 23 January 2021PDF Image | Recent Radial Turbine Research at Nasa Lewis 1972
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