Investigation of second generation controlled-diffusion compressor blades in cascade
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Authors
Hansen, Dennis J.
Subjects
Advisors
Hobson, Garth V.
Date of Issue
1995-09
Date
September 1995
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Detailed experimental investigation of second generation controlled-diffusion compressor stator blades at design inlet-flow angle was performed in a low-speed cascade wind tunnel using various experimental methods. Surface pressure measurements were obtained using three instrumented blades, from which coefficients of pressure were calculated. Laser-Doppler velocimetry was used to characterize the flow in the inlet, in the passage between two blades, in the boundary layer of the blades, and in the wake. A five-hole pressure probe was used to determine the loss coefficient and the axial-velocity-density ratio of the flow through the cascade. Although the blades produced significant lift, separated flow was discovered on the suction side of the blades at approximately fifty percent axial chord, which showed that the design was not totally successful. All the experimental measurements were performed at an inlet flow Mach number of 0.22 and a Reynolds number, based on chord length, of 640,000. Experimental blade-surface pressure coefficients were compared with values predicted using a computational fluid dynamics code. These initial predictions did not match well with the experimental results.
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Organization
Identifiers
NPS Report Number
Sponsors
Funding
NA
Format
126 p.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
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.