The high efficiencies of small radial turbines led to their application in space power systems and numerous APU and shaft power engines. Experimental and analytical work associated with these systems 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 variation consistent with minimum overall diffuser loss.
Document ID: 19720005135. Accession ID: 72N12784. E-6516. NASA-TM-X-67903. Gas Turbine Power and Fluids Eng. Div. Conf.; 26-30 Mar. 1972; San Francisco.
