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o 2.60 - E -- jQ -- - 2.50_ [_h_ •E 2.40 2.30 "_ "_ .> 2.20 "_ tu ..................... 800 .... , ................ .................... 4.0 4.5 200 ................ 4.0 4.5 I .... 5.5 6.0 Design E o .> _ ur 3.5 Equivalentinlettotal-to-exittotalpressureratio, 3.5 Equivalentinlettotal-to-exit totalpressureratio, Figure 20.--Variation of mass flow rate with total-to-total pressure ratio for lines of constant speed for rotor I-stator II Figure 22.--Variation of turbine torque with total-to-total pressure ratio for lines of constant speed for rotor I-stator II configuration. and 2.5 points lower than the design value of 91 percent. The trends for the 100- and 110-percent speed lines between the first and second vane angle setting are the same, although the 90-percent speed line shows a lower overall efficiency. The peak efficiency of 0.89 occurred at 110-percent speed and at a pressure ratio of 5.5. Figure 24 shows the static pressure drop through the stage from stations 0 to 4. A similar pressure drop occurred in the two tests, about 50 percent of the static pressure drop being in the stator and rotor. configuration, b <,-1" 40 =o _ "_ _ 35 _'_ '_ O" LU 30 3.5 Design,_ _ _-/- _ Percent of design speed P_)/P_ P_/P_ _ 90 4.5 5.0 Equivalent inlet total-to-exit total pressure ratio, ................ 4.0 100 I .... 5.0 5.5 6.0 5.0 p_)/p_ Figure 21.--Variation of specific work with total-to-total pres- .90 sure ratio for lines of constant speed for rotor I-stator II _ configuration. _ Figure 21 shows the specific work as it varies with the pres- _ ¢ sure ratio for three speeds. These results are similar to those "_ .84 for the rotor I-stator I test. "5 I-- Figure 22 presents the corrected torque as a function of the stage pressure ratio for the three speeds. The torque measured at the design pressure ratio and speed was 549 in.-lb, 5 per- cent less than that for the rotor I-stator I test. As in the previ- ous test, limit loading did not occur for the rotor I-stator II configuration. In figure 23, the torque measurements were used to show the total efficiency of the rotor. At the design point, the effi- ciency was 0.885, the same as that for the rotor I-stator I test _ Percent of design speed 90 -- 100 110 ..O ,-- .-- ,_ _ 600 _ 0 ,_,,_._-_ e_ -'_r_ B_..-B'_ =_._" / ____._. _) ---- "B_--'-" _ [] o [] 110 5.5 6.0 _ Z_ 90 design speed -_ 0 100 [] 110 ET uJ .92 ...............D.e.s.i.g.n., 1 _ [] _ o - Q •_.86 _ [] "_ Percent of design speed Z_ 90 o 100 .82 .80 3.5 P()/P3 Figure 23.--Variationof total efficiency with total-to-total pressure ratio for lines of constant speed for rotor I- stator IIconfiguration. ................ 4.0 4.5 [] 11o I .... - 5.5 6.0 Equivalent inlet total-to-exit total pressure ratio, 5.0 13PDF Image | Aerodynamic Radial Inflow Turbine Rotors
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