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Recent Radial Turbine Research at the NASA Lewis Research Center H. E. ROHLIK M. G. KOFSKEY TI;TP.ODJC^_ION The high efficiencies of small radial in- flow turbines have resulted in their use in many APU's, small turboshaft engines, and space power systems. The selection and development of com- ponents for specific applications has required knowledge of Reynolds number effects, internal losses, blade-shroud clearance penalties, and other characteristics to assure adequate and safe operation. The Lewis Research Center of NASA began in 1962 to investigate components designed under contract for Brayton cycle space power systems. The studies included internal flow analyses, as well as experimental operation of compressors, turbines, alternators, and various combinations of these. The work in radial turbines from 1962 to 1967 was highlighted and summarized in refer- ence (1),l a paper presented at the Second Inter- society Energy Conversion Engineering Conference in August 1 9 6 7 . Since that time, work has con- tinued in the areas of blade-shroud clearance, blade loading, exit diffusers, and a specific speed investigation with various stator and rotor areas in a single turbine. Experiments have been made with cold air and argon and the high preci- sion instrumentation and procedures described in reference(2). This paper includes the major results ob- tained in several experimental programs concluded since 1967 and others still in progress. Detailed descriptions of the research hardware and the investigations may be found in the references listed. TEST EQUIPMENT The apparatus used in the performance eval- uations of the turbines to be discussed is shown 1 Numbers in parentheses designate References at end of paper. —Turbine working fluid from high pres- sure s supply Electric heater Pressure Choked-flow nozzle or control valve-i f-Air from high iwes - I 1. supply system _ 1 1 thin-plate orifice Gas filter Pressure control valve Alrbrake dynamometer To low-pressure exhaust system and control valves-\ Research turbine Fig. 1 Experimental equipment (2' in Fig. 1. Argon or air, from a high-pressure supply system, was passed through a calibrated orifice plate for flow measurement upstream of the turbine. Turbine inlet and exit pressures were controlled with automatic valves during data taking. An airbrake dynamometer, cradled on air bearings, was used to absorb power, control speed. and measure torque. Internal instrumentation: included static pressure taps, thermocouple rakes, and survey probes for flow angle and local total pressures and temperatures. Fig. 2 is a photograph of one of the tur- bines. It is typical of those investigated, with an inlet volute, conventional stator blades, and a rotor with full and splitter blades. Its tip diameter is 15.3 cm, while other test turbines discussed herein had diameters of 1 1 . 7 and 12.x; cm. These were all low pressure ratio machines, 1.5 to 1.8. 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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