Accession Number : ADA254827


Title :   Cooled High-Temperature Radial Turbine Program. Phase 2


Descriptive Note : Final contractor rept.,


Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER


Personal Author(s) : Snyder, Philip H


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a254827.pdf


Report Date : May 1992


Pagination or Media Count : 95


Abstract : The objective of this program was the design and fabrication of a air-cooled high-temperature radial turbine (HTRT) intended for experimental evaluation in a warm turbine test facility at the Lewis Research Center. The rotor and vane were designed to be tested as a scaled version (rotor diameter of 14.4 inches diameter) of a 8.021 inch diameter rotor designed to be capable of operating with a rotor inlet temperature (RIT) of 2300 deg. F, a nominal mass flow of 4.56 lbm/sec, a work level of equal or greater than 187 Btu/lbm, and an efficiency of 86% or greater. The rotor was also evaluated to determine it's feasibility to operate at 2500 deg F RIT. The rotor design conformed to the rotor blade flow path specified by NASA for compatibility with their test equipment. Fabrication was accomplished on three rotors, a bladeless rotor, a solid rotor, and an air-cooled rotor.


Descriptors :   *GAS TURBINES , *ENGINES , *RADIAL FLOW , TEST AND EVALUATION , VELOCITY , AERODYNAMIC CONFIGURATIONS , DIAMETERS , TEMPERATURE , STRESS ANALYSIS , HIGH TEMPERATURE , FACILITIES , AIR FLOW , AIR COOLED , ROTOR BLADES , TEST FACILITIES , INLETS , ROTORS , FLOW , WORK , TURBINES , MASS FLOW , PATHS , EFFICIENCY , FABRICATION , COMPATIBILITY , TEST EQUIPMENT , BLADES , SOLIDS


Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE