Design of a Rotor Incorporating Splitter Vanes for a High Pressure Ratio Supersonic Axial Compressor Stage
Interim rept. 1 Nov 1971-30 Mar 1972,
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OH
Pagination or Media Count:
This report describes a redesign of the rotor of a supersonic axial compressor stage. The original design operated with excessive deviation angles as incidence increased at part speed, and the compressor was never able to recover from this condition. The redesign incorporated splitter vanes consisting of reduced chord airfoils extending full span in the downstream half of each passage defined by the principal airfoils. A complete aerodynamic description of the stage is presented along with the detailed geometry of the new rotor, both on streamsurfaces and on manufacturing Cartesian planes.
- Jet and Gas Turbine Engines