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$3.00PERCOPY $1.00 TO ASME MEMBERS 72-GT-42 ' ' L'L' ' The Society shall not be responsible for statements or opinions advanced in papers or in discussion at meetings of the Society or of its Divisions or Sections, or printed in its publications. Discussion is printed only if the paper is published in an ASME journal or Proceedings. Released for general publication upon presentation. Full credit should be given to ASME, the Professional Division, and the author Is) Copyright©1972byASME Recent Radial Turbine Research at the NASA Lewis Research Center H. E. ROHLIK M. G. KOFSKEY Lewis Research Center, Cleveland, Ohio The high efficiencies of small racial turbines have led to their app cation H space power systems and numerous APU and shaft power engines. Experimental an analytical work associated with these systems has included examination of blade shroud clearance, blade loading, and exit diffuser design. Results indicate high efficiency over a wide range of specific speed and also insensitivity to clearance and blade loading in the radial part of the rotor. The exit diffuser investigation indicated that a conventional conical outer wall may not provide the velocity varia- tion consistent with minimum overall diffuser loss. A list of recentiv published NASA radial turbine reports is included. Contributed by the Gas Turbine Division of the American Society of Mechanical En- gineers for presentation at the Gas Turbine and Fluids Engineering Conference & Prod- ucts Show, March 26-30, 1972, San Francisco, Calif. lanuseript r^ c4'ived at A' "I i. Headquarters, December 10, 1971. Copies will be available until Janaury 1, 1973. THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS, UNITED ENGINEERING CENTER, 345 EAST 47th STREET, NEW YORK, N.Y. 10017 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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