Hotwire measurements of the turbulent flow into a cascade of controlled-diffusion compressor blades

Turbulence measurements near the leading edge of a compressor stator were made in a subsonic cascade wind tunnel with a hotwire system. Using a single hot-film probe, velocity and turbulence distortion data were obtained about the leading edge of the Controlled-Diffusion (CD) blades in order to verify Laser Doppler Velocimetry (LDV) data taken in earlier studies. Measurements were conducted at a Mach number of .25, a Reynolds number of 711000 and an inlet flow angle of 48 degrees. Turbulence profiles obtained in the pitch-wise direction were found to be in good agreement with previous LDV measurements. These data indicated a localized increase in turbulence around the leading edge due to the interaction of the free-shear layer with the inlet turbulence. This free-shear layer extends over the separation bubble, which forms on the suction side of the blades' leading edge.

Department dc:contributor.department

Department of Aeronautics and Astronautics

Grantor dc:publisher

Monterey, California. Naval Postgraduate School

Year dc:date.issued

1993

Author dc:creator

• Wakefield, Bryce Edwin.

Advisor dc:contributor.advisor

• Hobson, Garth V.

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.

Language dc:language.iso

en_US

Handle dc:identifier.uri

https://hdl.handle.net/10945/39753

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/39753