Flow Into a Transonic Compressor Rotor.
Interim rept. Jul 73-Jun 74,
NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
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An analytical representation is given for the axisymmetric 2-dimensional flow field at the face of a transonic rotor. Streamlines computed for irrotational inviscid flow are closely approximated using a curve-fitting technique, which is described, and boundary layer blockage is then introduced. With the inlet flow so represented, the conditions relative to the rotor blading of the TRANSX compressor are calculated as a function of the radius and graphed as a function of flow rate and rotor speed. The purpose of this report is to both document calculations carried out for the TRANSX compressor and to record useful analytical techniques and short programs developed.
- Hydraulic and Pneumatic Equipment
- Fluid Mechanics
- Jet and Gas Turbine Engines