All aircraft gas turbine engines currently compromise compression system performance at some point(s) 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.
Characterization of Stall Inception in High-Speed Single-Stage Compressors
1994
166 pages
Report
No indication
English
British Library Conference Proceedings | 1995
|Stall Inception in Single-Stage, Transonic Compressors with Straight and Swept Leading Edges
Online Contents | 1995
|