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TuCd U Fig. 2 Turbine rotor and scroll (3) .9 .8 1 6 in 8 \ \ 0246 Blade-shroud clearance, I,f rcent of passage heignt Fig. 4 Comparison of effect cr_ Static eif'icier c ; of clearance variation for three turbines. Uniform percent clearance at rotor en- trance and exit for radial-inflow-turbine Exit clearance_ percent 4 Q 0.25(min) 921 ref. 4 data) c 03 .4 3i I i I I I .2 .3 .4 .5 .6 .7 .8 Blade-jet speed ratio, v F i g . 3 Effect of uniform clearance values on static efficiency for varying blade-jet speed ratios (3) BLADE-SHROUD CLEARANCE EFFEC` The effect of blade-shroud clearance on tur- bine performance is of interest because of mass flow, blade loading, and efficiency considerations. The clearance must be adequate to avoid contacts during speed and thermal transients, but minimized to avoid blade unloading and excessive loss gener- ation. Besides this operational concern, knowledge is also desirable for better understanding of the flow and comparison with axial turbine clearance effects. A test program involving varying clear- ance and clearance distribution was carried out k1_ 1'. 9'. .. p. 0^\ ° 0 7 c^ ^ C uI 0~ \ -2F— \ - -6 \ W\ r1 I \ . ImpuI Iref. 7 80 Equal percent, exit and inlet clearance 4 8 12 16 Inlet clearance, percent of passage height \ ^R r,. Iref. o, \/\\ ,` \ Rau i' Fig. 5 Summary of inlet and exit clearar_ne effects on total efficiency at desi n equivalent values of speed and poess-.re ratio pressor of a two-shaft space power system. investigation, described in reference (3), in.- cluded step changes in clearance in the inlet: portion of the rotor and also in the exit por- tion. These were carried out so that separate trends could be established with local clears-.no change, as well as with uniform incremental changes in terms of percent of passage height. Minimum clearance was established by coat- ing the shroud with lacquer and hand finishing. Measurements showed about 0.25 percent of passar.e height from inlet to outlet for this minimum :e, i._3o;. ten_ 7 20 24 28 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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