THE AERODYNAMIC DESIGN OF A COMPRESSOR-DRIVE TURBINE FOR USE IN A 75 KW AUTOMOTIVE ENGINE

The design of a single stage axial-flow turbine with a tip diameter of 11.15 cm is presented. The design specifications are given, and the aerodynamic design procedure is described. The aerodynamic information includes the results of flow path, velocity diagram, and blade profile studies. Predicted off-design performance characteristics are also presented. (Author)

  • Corporate Authors:

    Lewis Research Center

    National Aeronautics and Space Administration
    Cleveland, OH  USA  44135
  • Authors:
    • Roelke, R J
    • Mclallin, K L
  • Publication Date: 1975-4

Media Info

  • Pagination: 39 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00091869
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-TM-X-71717
  • Files: TRIS
  • Created Date: Sep 10 1976 12:00AM