Characterization of Stall Inception in High-Speed Single-Stage Compressors.
Final rept. 1 Aug-1 Dec 92,
WRIGHT RESEARCH AND DEVELOPMENT CENTER WRIGHT-PATTERSON AFB OH AERO PROPULSION AND POWER LAB
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All aircraft gas turbine engines currently compromise compression system performance at some points in their operating envelope to obtain adequate stall margin. This work pursues the concept of active stall control to minirnize or eliminate this penalty, thereby improving the performance of any aircraft gas turbine engine.
- Jet and Gas Turbine Engines