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blades on ...e ohro..d ad ..ell ;,o.0' l r,_ e aplT tier blades along the hub. Also, velocities near the inlet are quite low. An examination of internal losses, based on flow measurements, showed that rotor losses increased by about 0.006 in total efficiency in reducing the flow areas from design values to the 42 to 53 percent combination. Over- all efficiency decreased from 0.930 to 0.895 with the loss increase occurring largely in the stator. Fig. 17 shows the internal flow velocities calculated for the high flow (144 to 137 percent) case. The velocity levels upstream of the throat are considerably higher than in the low flow case, indicating higher blade loading, lower reaction, and all velocities well above zero, i.e., no flow eddy. Total efficiency was 0.92, indicating very slight increases in stator and rotor viscous losses over those of the design area confif;iara- tion. This investigation indicated a: air that radial turbines are relatively insensitive to unfavorable flow conditions in the upstream part of the rotor passages. CONCLUDING REMARKS The radial turbine effort began at the Lewis Research Center as technical support for the Brayton cycle space power program, The intent was to learn more about the performance characteristics in order to increase efficiency and to properly assess losses where compromises might result from mechanical and thermal consid- erations or any other operational requirements. The analytical techniques in flow analysis, off-design performance estimation, etc., and experimental information have been helpful in system studies and advanced component designs. The radial turbine program is continuing in support of both the Brayton cycle space power program and advanced small airbreathing engine programs involving such applications as heli- copter, APU, vehicular, etc. One effort in process involves an advanced turbine suitable for the 2- to 10-kw single-shaft system. The design employed knowledge obtained in the radial turbine studies, as well as some axial turbine investigations. The turbine has stators with converging endwalls for low-velocity turning, no cal i+,tens, a,.d tandem rotor blades. .. second effort is the study of the effect of rotor tip cutback on radial turbine performance. Other studies under way are directed at problems associated with high-temperature cooled radial turbines. One such design is currentl-; under way that includes a low blade number, no splitters, and very thick leading edges at re- duced diameter to accommodate cooling and resist erosion damage. Another area of effort is that of radial turbine erosion and methods for its reduction. These programs are directed at achiev- i n g the reliability and structural integrity required for these small turbines while maintain- ing the high efficiency levels associated with more conventional radial turbines. 1 F'ohlik, F. E., P,ofske;;, :',. and Katsanis, T., "Summary of NASA Radial Turbine Research Related to Brayton Cycle Space Power Systems," TM X-52298, NASA, Cleveland, Ohio, 197. 2 Futral, S. M., Kofskey, M. G., and Rohlik, H. E., "Instrumentation Used to Define Performance of Small Size, Low Power Gas Turbines,' TM X-52522, NASA, Cleveland, Ohio. 3 Futral, S. M. Jr., and Holeski, D. E. "Experimental Results of Varying the Blade-Shroud Clearance in a 6.02-Inch Radial Inflow Turbine," TN D-5513, NASA, Cleveland, Ohio, 1970. 4 Futral, S. M., Jr., and Wasserbauer, C. A., "Experimental Performance Evaluation of a 4.59-Inch Radial-Inflow Turbine With and Wii;h- out Splitter Blades," TN D-7015, NASA, Cleveland, Ohio, 1970. 5 Nusbaum, W. J., and Kofskey, M. C., "Radial-Inflow Turbine Performance with Exit Diffusers Designed for Linear Static Pressure Variation," TM X-2357, NASA, Cleveland, Ohio, 1971. 6 Nusbaum, W. J., and Kofskey, M. G., "Cold Performance Evaluation of a 4.97-Inch Radial- Inflow Turbine Designed for a Single-Shaft Bray- ton Cycle Space-Power System," TN D -5090, NASA, Cleveland, Ohio. 7 Kofskey, M. G., and Nusbaum, W. C. "Effects of Specific Speed on the Experimental Performance of a Radial-Inflow Ta.?rbire," Proposed Technical Note. B 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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