Single-Stage Axial Compressor for the Study of Rotating Stall Suppression
Conference Paper
Overview
Identity
Other
View All
Overview
abstract
Rotating stall and surge are flow instabilities that have plagued jet engines since the early days of their development. With the growing need for higher efficiencies, compressors are required to operate closer to the surge line. The breakdown of the flow into either rotating stall or surge is undesirable due to the effects it has on the jet engines performance and reliability. The traditional methods only partially protect against rotating stall or reduce compressor efficiency. This paper presents a single-stage axial compressor design that will be used to test a stall suppression system which introduces oscillatory blowing through one of the rotor blades.
