The subject of this paper is the assessment of developments in axial flow compressor, centrifugal compressor, and axial-flow turbine. The emphasis is put on modern calculation methods of the fluid flow within the turbomachinery, which often use computer programs. These methods can be divided in two groups: the direct or analytical method which gives the velocity distribution for a given channel shape; the indirect or design method which designs the turbomachinery for a prescribed velocity distribution. The turbomachine performance is evaluated by using correlations of experimental data and by computing directly the losses, at design as well as at off-design point. Because of the adverse pressure gradient, the compressor losses are greatly affected by the boundary layer which can cause separation of the flow. Local adverse pressure gradients may exist in the turbine channel. For supersonic compressor and turbine designs shock waves can induce important losses. Turbomachine stall and surge problems are also reviewed.

  • Corporate Authors:

    Massachusetts Institute of Technology

    Department of Ocean Engineering, 77 Massachusetts Avenue
    Cambridge, MA  United States  02139
  • Authors:
    • Tatibouet, J
  • Publication Date: 1973-5

Subject/Index Terms

Filing Info

  • Accession Number: 00048351
  • Record Type: Publication
  • Source Agency: Massachusetts Institute of Technology
  • Report/Paper Numbers: MS Thesis
  • Files: TRIS
  • Created Date: Nov 14 1973 12:00AM