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1.0 .6 =_. .o_ .4 _ .2 , , Equivalent pressureratio, 100 ......... ' o i o - o n .8 _k 80 6 4.0_o t_O 0 Percentmeridionaldistanceon shroud Figure17._Shroud staticpressuresoverrotorIforvarious pressureratiosat designrotorspeed. Stator II Exit Surveys Because the first test configuration showed a 5.6 percent higher mass flow than the design intent, the stator area was closed down to obtain the correct design mass flow. After the stator vanes were restaggered by 1.125", the stator exit flow was surveyed spanwise and circumferentially. Figures 18 and 19 show the survey results for the closed-down stator II at the design condition. Figure 18(a) shows the circumferentially averaged, spanwise flow angle distribution; the design intent was 70*. Figure 18(b) shows the vane efficiency as it varies spanwise from 85 to 98 percent, Figure 19(a) presents the total pressure ratio contours in the stator exit plane. The survey covers approximately 15°, and it captures about 1 1/2 vane pitches. The contours show a low- loss core flow, a clearly defined wake, and a region of consid- erable total pressure loss near both endwalls. The loss patterns efficiency calculated in the stator exit plane. As seen in the previous pressure loss figure, the efficiency is high in the core are not symmetric about the midplane. Figure 19(b) shows the region whereas losses occur near the endwalls. Rotor I With Stator II The mass flow as a function of the inlet-to-exit total pres- 2.34 lbm/sec, which is within 1/2 percent of the design value. suurerer2a0ti.oTfohrethmeraostosrIf-lostwatoartlItchoenfdiegsuirgantiosnpiessehdowandinpfirge-ssure ratio is Data show that the turbine stage chokes at a pressure ratio of 5.0 for most speeds although choking may occur earlier for O .... 4.5 5.0 5.3 -__ 2---..... _ ............... i,,,,i, 0 50 100 150 a) Oi ........ i ......... i ......... i ......... Flow angle,cx,dee 100 '_ o' ' 80 o O O ..... e Q) 90 percent speed. Even with the closed-down stator II, the (b) maximum mass flow is still affected by the rotor speed, indi- eating a rotor rather than stator choke, 1 blade passage Figure 19.---Stator exit plane contours for design flow conditions. (a)Total pressure ratio. (b) Efficiency. 12 o ¢n 60 o "6 o Eo Design intent t- D.40 o 20 o t- [:2. 0 t ........ 67 68 69 70 71 72 60 o "6 o _o o 40 neo 20 ° ° o .00 b) ° 0.80 .......8...5....... .90 .95 Vane efficiency, n Figure 1&--Exit survey results for closed-down stator IIat design condition. (a) Circumferentially averaged flow angle at starer exit. (b)Circumferentially averaged span- wise variation of vane efficiency. ----_.___ .99 .97 _ (a) _'_9_7_"_9__ ____.......___ 1 blade passage .9___ .95 97 .99PDF Image | Aerodynamic Radial Inflow Turbine Rotors
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