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L vNix r 0 r ^- ^7,p,t -^^ O 3 L— 1 0 0 Equal percent, Inlet 4and exit clearance Exit clearance, Percent 0.25 (min 92 (ref. 4 data) 1250 Hub D Hub 50-Percent r Inlet clearance, percent of passage height 5 Fig. 60 Summary of inlet and exit clearance s u r f a c e / ^ Shroud pr effects on mass flow rate at design equivalent values of speed and pressure ratio (3) 0 ^1_^1..1_1-J^ Ll-L1_, .8 1.6 2.4 3.2 0 .8 1.6 2.d 3.2 Distance along meridional streamline, in. l __i_ Fig. 7 Rotor with splitter blades removed (4) efficiency dropped from 0.84 to 0.81 and then 0.77 as clearance was increased uniformly from 0.25 to 3.0 and 7.0. The effect on total effi- ciency was about the same. The increased clear- ances were obtained by removing the lacquer from the shroud and grinding material from the blade tips. The trend shown in Fig. 3 may be compared with similar trends in axial flow turbines. Fig. 4 shows the effect of clearance on the static efficiencies of this radial turbine and two axial flow turbines. The turbines had different design point clearances as shown and different sensitiv- ity to blade-shroud clearance. It should be noted that in all cases shown, the clearance was in- creased from the design value by removing blade material. The slopes of the curves show that the radial-inflow turbine was least sensitive to clearance change. One percent of passage height removed from the blade resulted in 1.3 percent loss in specific work output. Corresponding values for the impulse and reaction axial turbines were 1.8 and 3.0. a 7 8 6600 50-Percent streamline i3 150 40p p g3 2 5;0^404801216202428 W800,Shroud-Suction - oils 0246802468 Distance along meridional streamline, cm (a) Rotor with splitter (b) Rotor without splitter blades, blades. rig. 8 Gas relative velocities at blade surfree Fig. 5 shows the separated effects of inlet clearance and exit clearance on efficiency. The exit clearance is the more influential by a facer,, of ten in the 0 to 8 percent clearance range. Clearance near the trailing edge is obviously hbe controlling influence, determining that frac°.• or, of the flow that is fully turned to the exit blade angle. Since the turbine stator sets , p the available whirl, this means that the desin specific work is very nearly achieved, even wii-J, relatively large inlet clearances. The efficie c,; shows a slight drop because of the losses incurred in the clearance space. This would probably be true in the case of an axial turbine with extre - ly high solidity. The effects of inlet and exit clearance o mass flow are shown in Fig. 6. Here again, the exit clearance is most influential, since the exit flow area is the effective orifice in tie rotor. Reference ( 3) discusses these effects Cr. some detail and also includes the results of radial surveys of flow angle, total pressure. and total temperature at the herbine exit for cart clearance configuration, SPLITTER BLADE REMOVAL The effect of blade loading near the rotor inlet was examined experimentally in an 11.7-cm scale model of the turbine used in the clearance investigation. The splitter blades were removed, doubling the blade loading in the upstream half of the rotor, Fig. 7. Channel velocities were then calculated for both cases, with and witholo'-. splitters. The results are shown in Fig. 8. i`,:e negative velocities on the pressure side of the j ^ StreamInP, p er __ f `^ 600^//^, Pressure r ^/ j surface /°Suction surface pressure surface 9 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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