ANALYTICAL DESIGN OF AN ADVANCED RADIAL TURBINE

The aerodynamic and mechanical potential of a single stage ceramic radial inflow turbine was evaluated for a high temperature single stage automotive engine. The aerodynamic analysis utilizes a turbine system optimization technique to evaluate both radial and nonradial rotor blading. Selected turbine rotor configurations were evaluated mechanically with three dimensional finite element techniques. Results indicate that exceptionally high rotor tip speeds (2300 ft/sec) and performance potential are feasible with radial bladed rotors if the projected ceramic material properties are realized. Nonradial rotors reduced tip speed requirements (at constant turbine efficiency) but resulted in a lower cumulative probability of success due to higher blade and disk stresses.

  • Corporate Authors:

    Garret Corporation

    402 South 36th Street
    Phoenix, AZ  United States  85043

    National Aeronautics and Space Administration

    600 Independence Avenue, SW
    Washington, DC  United States  20546
  • Authors:
    • Large, G D
    • Finger, D G
    • Linder, C G
  • Publication Date: 1981-2

Media Info

  • Pagination: 155 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00337404
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-CR-165170 Final Rpt., DOE/NASA/0106-1
  • Contract Numbers: DEN3-106,, DE-AI01-77CS-51040
  • Files: TRIS
  • Created Date: Aug 15 1981 12:00AM