Near-Stall Loss Measurements in a CD Compressor Cascade with Exploratory Leading Edge Flow Control

Loss measurements were conducted using a five-hole conical pneumatic probe in a subsonic wind tunnel containing a modeled cascade of controlled diffusion (CD) stator blades. Following reference measurements at high incidence one blade was modified (slotted at the leading edge) in an attempt to (passively) reduce the size of the leading edge separation bubble and thereby improve performance. Prior to the surveys, the acquisition and reduction software was modified to provide loss calculations using both mass-averaged and fully-mixed-out conditions for the upstream and downstream flows. Results showed that the mass-averaged method provided the more consistent results, and this was explained. The slotted leading edge blade was found to produce less loss than the reference blade, and it was concluded that the control concept should be explored in more detail.

Department dc:contributor.department

Department of Aeronautics and Astronautics

Grantor dc:publisher

Monterey, California. Naval Postgraduate School

Year dc:date.issued

1990

Author dc:creator

• Armstrong, Jeffrey H.

Advisor dc:contributor.advisor

• Shreeve, Raymond P.

Statement dc:rights

• This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.

Handle dc:identifier.uri

https://hdl.handle.net/10945/44340

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/44340