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"= "_ _ -t___ -d 88- .86 .84 J _ dePseigrcnesnpteoefd - .- o=- "6 10 800 ....................... .92 .................... i. 600 E 400 tx----" Design uJ 200 ............ A 90 O 100 i .... _ 120 I .... .82 _ o 100 [] 110 Ix 120 - 5.0 5.5 6.0 3.5 Equivalent inlet total-to-exit total pressure ratio, P_)/P_ Figure 10.--Variation of turbine torque with total-to-total pressure ratio for lines of constant speed for rotor I-stator I configuration. The turbine total efficiency is shown in figure ll(a) as a function of the pressure ratio. The total efficiency varied from 0.83 to 0.892 of the maximum total efficiency, which occurs at 110 percent speed. At the design pressure ratio and speed, the efficiency measured 0.884, which is 2.6 percent lower than the predicted value. Figure ll(b) shows the total efficiency as a function of the work factor. Maximum efficiency is achieved at a work factor of 0.91 at 110 percent speed. At the design speed and pressure ratio, the work factor is 1.086 which is comparable to the design value of 1.099. Rotor exit surveys were made using station 4 probes to measure the radial variation in temperature, total pressure, and flow angles. The rotor was operated over the same series of speeds and pressure ratios as previously discussed in the overall performance testing. The data presented in figures 12 to 15 for the exit surveys are at design conditions. At off- design speeds and pressure ratios, the flow characteristics were similar to those observed at design conditions. These results are presented in appendix B. Figure 12 shows the flow angle data at station 4, down- stream of the rotor. The exit flow angle varied radially from -18" near the hub to -30* at the midpoint and at the tip. The flow angles are measured with respect to blade rotation. A greater average swirl angle was measured than the design intent of-20 °. The ratio of exit total temperature to inlet total temperature as it varies from hub to tip at the rotor exit is shown in figure 13. The hub region has 2 percent lower temperatures than the tip region, which suggests that there is a slightly higher work extraction near the hub. The ratio ofinlet total toexit total pressure asitvaries from hub to tip is presented in figure 14. The data show that there is a larger pressure drop in the tip area where unloading is occurring because of flow leakage through the tip region; however, the hub experiences less pressure drop. 4.0 4.5 5.0 5.5 6.0 3.5 4.0 4.5 Equivalent inlet total-to-exit total pressure ratio, Percentof designspeed 080 []110 _O_O80 l- _ A90 -....r _" _ ,- "_ _ ._._1._... ,_,_=._ _ = t%....n., _..___a.__ - (b)................. .6 .8 1.0 1.2 1.4 1.6 .8 Work factor, gJAh_/U 2 "6 "E __(a) .80 ..................... .92 .90 .88 .86 .84 .82 .80 P_)/P_ ...... -'' I..... P'ercentof' design speed - <> 80 - z_ 90 -- _ S Ix 120 _J Figure 11.--Variation of total efficiency with total-to-total pressure ratio and work factor for lines of constant speed for rotor I-stator I configuration. (a) Total-to-total pressure ratio. (b) Work factor. 100 80 60 _ 40 I:L 20 0 --40 zxe .... zx zx A zx zx _• zx zx ,, • Design intent e.- zx _'-- -20 ' ' ' ' , ' . , , 0 20 40 Flow angle, o_,deg Figure 12.--Radial variation of exit flow angle at design operating condition for rotor I-stator I configuration. • Design _ O 100 - [] 110 - -PDF Image | Aerodynamic Radial Inflow Turbine Rotors
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