Experimental and numerical investigation of second-generation, controlled-diffusion, compressor blades in cascade
Contributors: Naval Postgraduate School (U.S.) 
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1997
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 75
Subjects: CASCADES (FLUID DYNAMICS); COMPRESSOR BLADES
Description: This thesis contains a detailed experimental and numerical investigation of second-generation, controlled-diffusion, compressor-stator blades at an off-design inlet-flow angle of 39%5c Investigation of the blades took place in a low-speed cascade wind tunnel using various experimental procedures. The objective of the wind tunnel study was to characterize the flow field in and around the blades at the off-design angle, and to investigate flow separation near the mid-chord for a high Reynolds number of 640,000. Rake probe survey's were performed upstream and downstream of the lades in order to obtain spanwise total pressure profiles. Surface flow visualization was performed on the blades using a titanium dioxide and kerosene mixture. Blade surface pressure measurements were obtained using a 40-hole instrumented blade from which coefficients of    pressure were calculated. A standard optics, two-component, laser-Doppler velocimeter was used to characterize the flow field upstream, in the boundary layer on the suction side of the blades, and in the wake region. A numerical investigation was conducted using the rotor viscous code 3-D developed by Dr. Roderick Chima of NASA Lewis  Research Center. Overall, good  agreement between flow visualization, blade pressure      measurements, laser measurements, and numerical modeling was obtained.
Notes: Thesis advisor, Garth V. Hobson.

Thesis (M.S. in Operations Research) Naval Postgraduate School, March 1997.

Includes bibliographical references (p. 59)

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dk/dk cc:9116 02/03/98.